GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.8 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe647-il-1000000.txt Download as CSV file: xf-goe647-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6563 0.08046 0.07806 -0.0723 1.0000 0.0246
-15.500 -0.7216 0.06718 0.06455 -0.0815 1.0000 0.0246
-15.250 -0.7578 0.05902 0.05623 -0.0870 1.0000 0.0246
-15.000 -0.7835 0.05273 0.04983 -0.0910 1.0000 0.0246
-14.750 -0.8064 0.04703 0.04399 -0.0947 1.0000 0.0246
-14.500 -0.8233 0.04236 0.03921 -0.0978 1.0000 0.0247
-14.250 -0.8477 0.03767 0.03438 -0.1002 1.0000 0.0247
-14.000 -0.8594 0.03154 0.02801 -0.1081 0.9966 0.0250
-13.750 -0.8435 0.02917 0.02553 -0.1113 0.9920 0.0253
-13.500 -0.8250 0.02772 0.02402 -0.1124 0.9866 0.0255
-13.250 -0.7990 0.02647 0.02273 -0.1142 0.9830 0.0258
-13.000 -0.7743 0.02529 0.02148 -0.1154 0.9785 0.0260
-12.750 -0.7496 0.02432 0.02044 -0.1163 0.9729 0.0263
-12.500 -0.7208 0.02329 0.01932 -0.1178 0.9694 0.0267
-12.250 -0.6933 0.02240 0.01836 -0.1189 0.9631 0.0270
-12.000 -0.6609 0.02155 0.01741 -0.1207 0.9579 0.0275
-11.750 -0.6263 0.02058 0.01634 -0.1230 0.9531 0.0278
-11.500 -0.5973 0.01978 0.01543 -0.1240 0.9427 0.0281
-11.250 -0.5667 0.01915 0.01469 -0.1250 0.9323 0.0283
-11.000 -0.5400 0.01843 0.01383 -0.1254 0.9198 0.0286
-10.750 -0.5229 0.01712 0.01240 -0.1242 0.9051 0.0291
-10.500 -0.5024 0.01654 0.01175 -0.1231 0.8914 0.0294
-10.250 -0.4806 0.01612 0.01128 -0.1221 0.8792 0.0298
-10.000 -0.4584 0.01574 0.01081 -0.1210 0.8674 0.0302
-9.750 -0.4367 0.01535 0.01035 -0.1199 0.8558 0.0305
-9.500 -0.4149 0.01492 0.00984 -0.1188 0.8452 0.0309
-9.250 -0.3925 0.01457 0.00939 -0.1177 0.8338 0.0313
-9.000 -0.3698 0.01419 0.00895 -0.1166 0.8233 0.0316
-8.750 -0.3473 0.01385 0.00851 -0.1155 0.8112 0.0320
-8.500 -0.3245 0.01355 0.00811 -0.1143 0.7973 0.0323
-8.250 -0.3009 0.01331 0.00777 -0.1133 0.7830 0.0326
-8.000 -0.2796 0.01282 0.00719 -0.1120 0.7692 0.0330
-7.750 -0.2584 0.01233 0.00663 -0.1107 0.7564 0.0337
-7.500 -0.2350 0.01202 0.00627 -0.1097 0.7431 0.0341
-7.250 -0.2110 0.01176 0.00595 -0.1088 0.7302 0.0346
-7.000 -0.1868 0.01153 0.00565 -0.1079 0.7176 0.0351
-6.500 -0.1379 0.01113 0.00510 -0.1062 0.6903 0.0363
-6.250 -0.1130 0.01095 0.00484 -0.1053 0.6774 0.0368
-6.000 -0.0880 0.01082 0.00462 -0.1045 0.6655 0.0372
-5.750 -0.0640 0.01051 0.00425 -0.1036 0.6540 0.0380
-5.500 -0.0392 0.01030 0.00400 -0.1028 0.6430 0.0391
-5.000 0.0121 0.01003 0.00362 -0.1015 0.6221 0.0411
-4.750 0.0377 0.00994 0.00346 -0.1008 0.6127 0.0420
-4.500 0.0637 0.00975 0.00324 -0.1002 0.6038 0.0435
-4.250 0.0891 0.00963 0.00307 -0.0995 0.5943 0.0455
-4.000 0.1156 0.00953 0.00293 -0.0990 0.5847 0.0475
-3.750 0.1411 0.00941 0.00278 -0.0983 0.5756 0.0509
-3.500 0.1674 0.00927 0.00264 -0.0977 0.5666 0.0566
-3.250 0.1927 0.00914 0.00253 -0.0971 0.5574 0.0690
-3.000 0.2184 0.00898 0.00243 -0.0964 0.5469 0.0895
-2.750 0.2440 0.00888 0.00234 -0.0958 0.5369 0.1045
-2.500 0.2694 0.00878 0.00225 -0.0952 0.5263 0.1206
-2.250 0.2940 0.00857 0.00218 -0.0944 0.5164 0.1661
-2.000 0.3190 0.00851 0.00217 -0.0937 0.5050 0.1986
-1.750 0.3450 0.00850 0.00216 -0.0931 0.4922 0.2152
-1.500 0.3708 0.00852 0.00216 -0.0925 0.4797 0.2283
-1.250 0.3963 0.00857 0.00216 -0.0919 0.4667 0.2393
-1.000 0.4213 0.00862 0.00218 -0.0912 0.4531 0.2519
-0.750 0.4470 0.00866 0.00219 -0.0906 0.4400 0.2623
-0.500 0.4722 0.00872 0.00222 -0.0899 0.4270 0.2763
-0.250 0.4967 0.00876 0.00226 -0.0891 0.4141 0.2976
0.000 0.5207 0.00881 0.00232 -0.0882 0.4004 0.3228
0.250 0.5452 0.00886 0.00237 -0.0874 0.3878 0.3457
0.500 0.5698 0.00891 0.00244 -0.0867 0.3771 0.3689
0.750 0.5935 0.00899 0.00252 -0.0858 0.3663 0.3962
1.000 0.6184 0.00903 0.00259 -0.0851 0.3581 0.4235
1.250 0.6421 0.00913 0.00269 -0.0842 0.3494 0.4484
1.500 0.6671 0.00916 0.00276 -0.0834 0.3434 0.4726
1.750 0.6909 0.00924 0.00285 -0.0826 0.3367 0.4961
2.000 0.7144 0.00929 0.00295 -0.0816 0.3308 0.5248
2.250 0.7372 0.00924 0.00304 -0.0806 0.3261 0.5759
2.500 0.7532 0.00898 0.00317 -0.0781 0.3215 0.7236
2.750 0.8659 0.00891 0.00358 -0.0964 0.3121 0.9893
3.000 0.9073 0.00910 0.00373 -0.0993 0.3074 1.0000
3.250 0.9288 0.00927 0.00384 -0.0980 0.3034 1.0000
3.500 0.9492 0.00947 0.00399 -0.0965 0.2987 1.0000
3.750 0.9724 0.00956 0.00408 -0.0954 0.2966 1.0000
4.000 0.9949 0.00969 0.00419 -0.0943 0.2938 1.0000
4.250 1.0169 0.00983 0.00430 -0.0931 0.2907 1.0000
4.500 1.0380 0.01001 0.00445 -0.0918 0.2874 1.0000
4.750 1.0580 0.01023 0.00462 -0.0902 0.2835 1.0000
5.000 1.0798 0.01037 0.00477 -0.0890 0.2812 1.0000
5.250 1.1023 0.01050 0.00490 -0.0879 0.2792 1.0000
5.500 1.1242 0.01065 0.00504 -0.0868 0.2767 1.0000
5.750 1.1448 0.01082 0.00520 -0.0854 0.2738 1.0000
6.000 1.1630 0.01102 0.00537 -0.0835 0.2710 1.0000
6.250 1.1792 0.01127 0.00559 -0.0813 0.2675 1.0000
6.500 1.1982 0.01145 0.00578 -0.0796 0.2655 1.0000
6.750 1.2190 0.01160 0.00594 -0.0783 0.2639 1.0000
7.000 1.2396 0.01177 0.00612 -0.0770 0.2620 1.0000
7.250 1.2599 0.01196 0.00632 -0.0757 0.2600 1.0000
7.500 1.2796 0.01219 0.00654 -0.0743 0.2578 1.0000
7.750 1.2987 0.01245 0.00679 -0.0728 0.2554 1.0000
8.000 1.3163 0.01277 0.00710 -0.0712 0.2527 1.0000
8.250 1.3341 0.01311 0.00744 -0.0696 0.2503 1.0000
8.500 1.3556 0.01331 0.00768 -0.0687 0.2492 1.0000
8.750 1.3765 0.01355 0.00794 -0.0677 0.2477 1.0000
9.000 1.3971 0.01380 0.00821 -0.0667 0.2459 1.0000
9.250 1.4171 0.01408 0.00851 -0.0657 0.2441 1.0000
9.500 1.4361 0.01442 0.00886 -0.0645 0.2423 1.0000
9.750 1.4545 0.01479 0.00924 -0.0633 0.2405 1.0000
10.000 1.4711 0.01526 0.00971 -0.0619 0.2382 1.0000
10.250 1.4856 0.01585 0.01030 -0.0602 0.2354 1.0000
10.500 1.5073 0.01609 0.01059 -0.0596 0.2340 1.0000
10.750 1.5274 0.01643 0.01097 -0.0588 0.2324 1.0000
11.000 1.5468 0.01680 0.01138 -0.0580 0.2306 1.0000
11.250 1.5652 0.01723 0.01183 -0.0570 0.2284 1.0000
11.500 1.5823 0.01775 0.01237 -0.0560 0.2265 1.0000
11.750 1.5978 0.01837 0.01299 -0.0548 0.2242 1.0000
12.000 1.6096 0.01920 0.01382 -0.0533 0.2206 1.0000
12.250 1.6300 0.01957 0.01425 -0.0528 0.2191 1.0000
12.500 1.6490 0.02004 0.01476 -0.0522 0.2168 1.0000
12.750 1.6661 0.02061 0.01537 -0.0514 0.2141 1.0000
13.000 1.6810 0.02133 0.01612 -0.0504 0.2118 1.0000
13.250 1.6935 0.02223 0.01702 -0.0493 0.2089 1.0000
13.500 1.7049 0.02321 0.01803 -0.0481 0.2060 1.0000
13.750 1.7226 0.02381 0.01869 -0.0476 0.2044 1.0000
14.000 1.7385 0.02453 0.01947 -0.0469 0.2021 1.0000
14.250 1.7520 0.02542 0.02039 -0.0461 0.1990 1.0000
14.500 1.7619 0.02660 0.02157 -0.0451 0.1954 1.0000
14.750 1.7697 0.02796 0.02296 -0.0441 0.1924 1.0000
15.000 1.7856 0.02874 0.02381 -0.0436 0.1900 1.0000
15.250 1.7971 0.02986 0.02497 -0.0429 0.1862 1.0000
15.500 1.8043 0.03137 0.02649 -0.0420 0.1822 1.0000
15.750 1.8110 0.03294 0.02810 -0.0412 0.1781 1.0000
16.000 1.8203 0.03434 0.02955 -0.0406 0.1735 1.0000
16.250 1.8203 0.03658 0.03178 -0.0397 0.1670 1.0000
16.500 1.8248 0.03848 0.03372 -0.0391 0.1608 1.0000
16.750 1.8202 0.04127 0.03650 -0.0383 0.1531 1.0000
17.000 1.8123 0.04446 0.03969 -0.0376 0.1431 1.0000
17.250 1.7939 0.04880 0.04400 -0.0369 0.1312 1.0000
17.500 1.7771 0.05316 0.04836 -0.0366 0.1216 1.0000
17.750 1.7570 0.05798 0.05320 -0.0364 0.1130 1.0000
18.000 1.7326 0.06349 0.05875 -0.0365 0.1053 1.0000
18.250 1.7087 0.06910 0.06440 -0.0368 0.0986 1.0000
18.500 1.6830 0.07513 0.07050 -0.0375 0.0920 1.0000
18.750 1.6575 0.08131 0.07673 -0.0384 0.0874 1.0000
19.000 1.6267 0.08829 0.08378 -0.0396 0.0810 1.0000
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