GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 626 AIRFOIL (goe626-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.28 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe626-il-1000000.txt Download as CSV file: xf-goe626-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 626 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.7819 0.12369 0.12084 -0.0577 1.0000 0.0245
-19.500 -0.7921 0.11876 0.11583 -0.0602 1.0000 0.0247
-19.250 -0.7960 0.11486 0.11188 -0.0621 1.0000 0.0249
-19.000 -0.7955 0.11171 0.10871 -0.0635 1.0000 0.0250
-18.750 -0.7985 0.10796 0.10492 -0.0653 1.0000 0.0252
-18.500 -0.8006 0.10439 0.10131 -0.0670 1.0000 0.0253
-18.250 -0.8012 0.10118 0.09806 -0.0684 1.0000 0.0254
-18.000 -0.8022 0.09785 0.09469 -0.0699 1.0000 0.0256
-17.750 -0.8051 0.09426 0.09106 -0.0715 1.0000 0.0258
-17.500 -0.8060 0.09110 0.08786 -0.0728 1.0000 0.0259
-17.250 -0.8065 0.08809 0.08481 -0.0740 1.0000 0.0260
-17.000 -0.8092 0.08468 0.08136 -0.0755 1.0000 0.0263
-16.750 -0.8082 0.08206 0.07870 -0.0763 1.0000 0.0264
-16.500 -0.8077 0.07942 0.07602 -0.0770 1.0000 0.0266
-16.250 -0.8086 0.07653 0.07310 -0.0780 1.0000 0.0268
-16.000 -0.8095 0.07380 0.07033 -0.0788 1.0000 0.0269
-15.750 -0.8091 0.07139 0.06789 -0.0792 1.0000 0.0271
-15.500 -0.8084 0.06914 0.06561 -0.0794 1.0000 0.0272
-15.250 -0.8096 0.06673 0.06317 -0.0797 1.0000 0.0273
-15.000 -0.8119 0.06435 0.06075 -0.0798 1.0000 0.0275
-14.750 -0.8138 0.06221 0.05859 -0.0795 1.0000 0.0276
-14.500 -0.8167 0.06027 0.05663 -0.0789 1.0000 0.0276
-14.250 -0.8108 0.05781 0.05413 -0.0806 0.9994 0.0278
-14.000 -0.7972 0.05482 0.05108 -0.0846 0.9981 0.0279
-13.750 -0.7817 0.05217 0.04839 -0.0883 0.9964 0.0280
-13.500 -0.7666 0.04934 0.04550 -0.0927 0.9944 0.0281
-13.250 -0.7452 0.04823 0.04442 -0.0946 0.9929 0.0287
-13.000 -0.7328 0.04600 0.04218 -0.0973 0.9896 0.0289
-12.750 -0.7196 0.04340 0.03957 -0.1011 0.9858 0.0292
-12.500 -0.7043 0.04035 0.03650 -0.1063 0.9826 0.0294
-12.250 -0.6962 0.03704 0.03315 -0.1112 0.9767 0.0295
-12.000 -0.6811 0.03291 0.02895 -0.1188 0.9707 0.0297
-11.750 -0.6557 0.02846 0.02441 -0.1286 0.9678 0.0300
-11.500 -0.6331 0.02441 0.02025 -0.1360 0.9617 0.0303
-11.250 -0.6028 0.02095 0.01666 -0.1426 0.9576 0.0305
-11.000 -0.5701 0.01911 0.01472 -0.1466 0.9545 0.0309
-10.750 -0.5373 0.01786 0.01338 -0.1495 0.9511 0.0312
-10.500 -0.5146 0.01697 0.01242 -0.1498 0.9435 0.0315
-10.250 -0.4837 0.01614 0.01152 -0.1514 0.9387 0.0318
-10.000 -0.4560 0.01553 0.01084 -0.1521 0.9325 0.0321
-9.750 -0.4312 0.01468 0.00991 -0.1524 0.9249 0.0325
-9.500 -0.4038 0.01384 0.00896 -0.1533 0.9186 0.0331
-9.250 -0.3803 0.01323 0.00830 -0.1529 0.9107 0.0336
-9.000 -0.3526 0.01271 0.00769 -0.1532 0.9032 0.0341
-8.750 -0.3275 0.01227 0.00720 -0.1528 0.8951 0.0346
-8.500 -0.3007 0.01188 0.00673 -0.1528 0.8875 0.0352
-8.250 -0.2738 0.01153 0.00632 -0.1526 0.8810 0.0357
-8.000 -0.2474 0.01121 0.00595 -0.1524 0.8737 0.0363
-7.750 -0.2200 0.01091 0.00556 -0.1522 0.8667 0.0370
-7.500 -0.1937 0.01054 0.00516 -0.1520 0.8597 0.0383
-7.250 -0.1669 0.01023 0.00480 -0.1517 0.8518 0.0398
-7.000 -0.1397 0.00996 0.00449 -0.1515 0.8444 0.0420
-6.750 -0.1142 0.00940 0.00400 -0.1512 0.8360 0.0608
-6.500 -0.0878 0.00900 0.00365 -0.1509 0.8274 0.0837
-6.250 -0.0613 0.00866 0.00334 -0.1506 0.8179 0.0986
-6.000 -0.0351 0.00827 0.00301 -0.1503 0.8079 0.1220
-5.750 -0.0093 0.00783 0.00267 -0.1500 0.7961 0.1559
-5.500 0.0171 0.00758 0.00248 -0.1496 0.7829 0.1815
-5.250 0.0436 0.00748 0.00238 -0.1491 0.7669 0.1996
-5.000 0.0701 0.00746 0.00232 -0.1485 0.7469 0.2107
-4.750 0.0954 0.00753 0.00228 -0.1477 0.7185 0.2187
-4.500 0.1198 0.00764 0.00226 -0.1467 0.6856 0.2253
-4.250 0.1447 0.00779 0.00228 -0.1457 0.6601 0.2307
-3.750 0.1982 0.00796 0.00227 -0.1447 0.6303 0.2376
-3.500 0.2252 0.00802 0.00229 -0.1442 0.6192 0.2414
-3.250 0.2528 0.00810 0.00233 -0.1439 0.6096 0.2449
-3.000 0.2803 0.00820 0.00238 -0.1435 0.6007 0.2485
-2.750 0.3086 0.00830 0.00243 -0.1433 0.5933 0.2511
-2.500 0.3358 0.00833 0.00241 -0.1429 0.5853 0.2540
-2.250 0.3637 0.00833 0.00242 -0.1426 0.5784 0.2573
-2.000 0.3915 0.00839 0.00246 -0.1423 0.5702 0.2598
-1.750 0.4188 0.00849 0.00251 -0.1419 0.5611 0.2626
-1.500 0.4467 0.00856 0.00256 -0.1416 0.5520 0.2652
-1.250 0.4737 0.00865 0.00259 -0.1412 0.5432 0.2669
-1.000 0.5018 0.00869 0.00260 -0.1409 0.5352 0.2680
-0.500 0.5557 0.00871 0.00256 -0.1401 0.5155 0.2732
-0.250 0.5821 0.00878 0.00258 -0.1396 0.5037 0.2752
0.000 0.6089 0.00884 0.00260 -0.1391 0.4921 0.2767
0.250 0.6357 0.00890 0.00263 -0.1387 0.4820 0.2781
0.500 0.6620 0.00899 0.00267 -0.1381 0.4717 0.2797
0.750 0.6888 0.00906 0.00271 -0.1377 0.4627 0.2814
1.000 0.7150 0.00916 0.00276 -0.1371 0.4532 0.2829
1.250 0.7416 0.00923 0.00281 -0.1367 0.4452 0.2841
1.500 0.7679 0.00933 0.00286 -0.1361 0.4369 0.2851
1.750 0.7941 0.00943 0.00293 -0.1356 0.4295 0.2860
2.000 0.8206 0.00952 0.00300 -0.1351 0.4221 0.2866
2.250 0.8456 0.00958 0.00301 -0.1344 0.4129 0.2896
2.500 0.8717 0.00964 0.00307 -0.1339 0.4037 0.2921
2.750 0.8966 0.00977 0.00316 -0.1331 0.3949 0.2939
3.000 0.9231 0.00983 0.00324 -0.1327 0.3890 0.2957
3.250 0.9487 0.00994 0.00333 -0.1320 0.3828 0.2973
3.500 0.9737 0.01007 0.00343 -0.1313 0.3764 0.2991
3.750 0.9998 0.01015 0.00352 -0.1308 0.3703 0.3009
4.000 1.0245 0.01029 0.00362 -0.1300 0.3630 0.3024
4.250 1.0494 0.01041 0.00374 -0.1293 0.3559 0.3037
4.500 1.0743 0.01054 0.00385 -0.1286 0.3485 0.3048
4.750 1.0979 0.01068 0.00396 -0.1276 0.3416 0.3078
5.000 1.1231 0.01074 0.00406 -0.1270 0.3364 0.3112
5.250 1.1467 0.01088 0.00420 -0.1260 0.3291 0.3139
5.500 1.1691 0.01104 0.00434 -0.1248 0.3224 0.3163
5.750 1.1920 0.01116 0.00447 -0.1237 0.3155 0.3187
6.000 1.2124 0.01137 0.00463 -0.1222 0.3065 0.3209
6.250 1.2348 0.01151 0.00478 -0.1210 0.2985 0.3228
6.500 1.2549 0.01175 0.00498 -0.1195 0.2889 0.3256
6.750 1.2758 0.01195 0.00517 -0.1181 0.2785 0.3299
7.000 1.2953 0.01222 0.00542 -0.1165 0.2660 0.3336
7.250 1.3132 0.01258 0.00571 -0.1147 0.2495 0.3374
7.500 1.3276 0.01311 0.00610 -0.1123 0.2261 0.3407
7.750 1.3377 0.01382 0.00664 -0.1092 0.1954 0.3442
8.000 1.3507 0.01439 0.00713 -0.1067 0.1782 0.3508
8.250 1.3656 0.01486 0.00756 -0.1046 0.1684 0.3574
8.500 1.3827 0.01524 0.00796 -0.1028 0.1623 0.3667
8.750 1.3996 0.01561 0.00836 -0.1010 0.1576 0.3796
9.250 1.4326 0.01634 0.00926 -0.0974 0.1488 0.4457
9.500 1.4495 0.01661 0.00972 -0.0957 0.1452 0.5339
9.750 1.4699 0.01644 0.01036 -0.0950 0.1400 1.0000
10.000 1.4855 0.01694 0.01085 -0.0932 0.1346 1.0000
10.250 1.5001 0.01752 0.01139 -0.0913 0.1270 1.0000
10.500 1.5129 0.01819 0.01203 -0.0893 0.1173 1.0000
10.750 1.5101 0.01970 0.01331 -0.0854 0.0869 1.0000
11.000 1.5075 0.02129 0.01478 -0.0818 0.0701 1.0000
11.250 1.5148 0.02239 0.01587 -0.0795 0.0657 1.0000
11.500 1.5247 0.02338 0.01687 -0.0776 0.0632 1.0000
11.750 1.5336 0.02445 0.01797 -0.0757 0.0614 1.0000
12.000 1.5412 0.02566 0.01920 -0.0738 0.0596 1.0000
12.250 1.5491 0.02690 0.02047 -0.0720 0.0583 1.0000
12.500 1.5569 0.02820 0.02180 -0.0703 0.0573 1.0000
12.750 1.5669 0.02937 0.02302 -0.0690 0.0567 1.0000
13.000 1.5759 0.03067 0.02437 -0.0676 0.0562 1.0000
13.250 1.5834 0.03213 0.02588 -0.0663 0.0557 1.0000
13.500 1.5902 0.03370 0.02751 -0.0650 0.0550 1.0000
13.750 1.5964 0.03540 0.02926 -0.0639 0.0546 1.0000
14.000 1.6011 0.03730 0.03121 -0.0628 0.0542 1.0000
14.250 1.6052 0.03934 0.03331 -0.0619 0.0536 1.0000
14.500 1.6080 0.04160 0.03562 -0.0611 0.0530 1.0000
14.750 1.6095 0.04407 0.03816 -0.0605 0.0525 1.0000
15.000 1.6093 0.04683 0.04098 -0.0599 0.0519 1.0000
15.250 1.6063 0.04998 0.04421 -0.0596 0.0512 1.0000
15.500 1.6049 0.05303 0.04734 -0.0594 0.0510 1.0000
15.750 1.6053 0.05592 0.05030 -0.0593 0.0506 1.0000
16.000 1.6077 0.05862 0.05307 -0.0592 0.0504 1.0000
16.250 1.6092 0.06146 0.05599 -0.0593 0.0502 1.0000
16.500 1.6090 0.06458 0.05919 -0.0594 0.0500 1.0000
16.750 1.6090 0.06772 0.06240 -0.0597 0.0496 1.0000
17.000 1.6081 0.07103 0.06578 -0.0601 0.0493 1.0000
17.250 1.6070 0.07441 0.06925 -0.0605 0.0490 1.0000
17.500 1.6045 0.07808 0.07299 -0.0612 0.0487 1.0000
17.750 1.6021 0.08177 0.07675 -0.0619 0.0484 1.0000
18.000 1.6008 0.08534 0.08039 -0.0627 0.0480 1.0000
18.250 1.5978 0.08922 0.08434 -0.0636 0.0476 1.0000
18.500 1.5944 0.09322 0.08842 -0.0647 0.0473 1.0000
18.750 1.5913 0.09720 0.09246 -0.0658 0.0468 1.0000
19.000 1.5871 0.10138 0.09671 -0.0671 0.0464 1.0000
19.250 1.5811 0.10589 0.10129 -0.0686 0.0459 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 626 AIRFOIL (goe626-il)