GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 200,000 Max Cl/Cd: 72.43 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe374-il-200000.txt Download as CSV file: xf-goe374-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3385 0.09029 0.08694 -0.0164 1.0000 0.0213
-7.250 -0.3386 0.08795 0.08466 -0.0166 1.0000 0.0217
-7.000 -0.3363 0.08545 0.08221 -0.0177 1.0000 0.0220
-6.750 -0.3306 0.08294 0.07975 -0.0199 1.0000 0.0225
-6.500 -0.3224 0.08050 0.07733 -0.0229 1.0000 0.0228
-6.250 -0.3116 0.07808 0.07491 -0.0266 1.0000 0.0230
-6.000 -0.3000 0.07558 0.07239 -0.0292 1.0000 0.0231
-5.750 -0.2883 0.07306 0.06984 -0.0311 1.0000 0.0232
-5.500 -0.2777 0.07051 0.06724 -0.0318 1.0000 0.0233
-5.250 -0.2672 0.06795 0.06462 -0.0321 1.0000 0.0233
-5.000 -0.2567 0.06542 0.06201 -0.0320 1.0000 0.0234
-4.750 -0.2566 0.06061 0.05730 -0.0304 1.0000 0.0237
-4.500 -0.2544 0.05724 0.05398 -0.0286 1.0000 0.0240
-4.250 -0.2263 0.05303 0.04972 -0.0323 0.9961 0.0248
-4.000 -0.1878 0.04895 0.04553 -0.0377 0.9906 0.0259
-3.750 -0.1440 0.04495 0.04135 -0.0435 0.9850 0.0279
-3.500 -0.0822 0.04382 0.03959 -0.0489 0.9782 0.0312
-3.250 -0.0522 0.03749 0.03328 -0.0530 0.9723 0.0324
-3.000 -0.0168 0.03417 0.02987 -0.0564 0.9658 0.0341
-2.750 0.0236 0.03139 0.02686 -0.0596 0.9589 0.0371
-2.500 0.0709 0.02905 0.02397 -0.0623 0.9528 0.0422
-2.250 0.1054 0.02601 0.02093 -0.0651 0.9447 0.0468
-2.000 0.1425 0.02393 0.01859 -0.0670 0.9355 0.0584
-1.750 0.1806 0.02201 0.01642 -0.0690 0.9265 0.0719
-1.500 0.2139 0.02097 0.01502 -0.0696 0.9129 0.0954
-1.250 0.2413 0.01908 0.01309 -0.0701 0.8961 0.1240
-1.000 0.2661 0.01820 0.01214 -0.0699 0.8760 0.1792
-0.750 0.2895 0.01614 0.01020 -0.0696 0.8558 0.2302
-0.500 0.3167 0.01524 0.00906 -0.0685 0.8315 0.2482
-0.250 0.3585 0.01496 0.00783 -0.0661 0.8088 0.1065
0.000 0.3861 0.01387 0.00652 -0.0648 0.7822 0.0868
0.250 0.4127 0.01329 0.00569 -0.0634 0.7527 0.0746
0.500 0.4384 0.01289 0.00503 -0.0621 0.7216 0.0685
0.750 0.4635 0.01275 0.00469 -0.0609 0.6906 0.0669
1.000 0.4871 0.01222 0.00406 -0.0598 0.6625 0.0696
1.250 0.5112 0.01209 0.00379 -0.0588 0.6362 0.0691
1.500 0.5355 0.01205 0.00359 -0.0578 0.6127 0.0687
1.750 0.5601 0.01203 0.00345 -0.0570 0.5897 0.0692
2.000 0.5850 0.01208 0.00335 -0.0563 0.5700 0.0712
2.250 0.6103 0.01213 0.00330 -0.0556 0.5495 0.0754
2.500 0.6354 0.01219 0.00327 -0.0548 0.5300 0.0875
2.750 0.6841 0.01053 0.00337 -0.0597 0.5073 1.0000
3.000 0.7088 0.01076 0.00343 -0.0589 0.4901 1.0000
3.250 0.7334 0.01100 0.00353 -0.0582 0.4739 1.0000
3.500 0.7581 0.01127 0.00367 -0.0576 0.4591 1.0000
3.750 0.7829 0.01155 0.00387 -0.0569 0.4452 1.0000
4.000 0.8078 0.01182 0.00408 -0.0564 0.4328 1.0000
4.250 0.8326 0.01212 0.00431 -0.0558 0.4207 1.0000
4.500 0.8574 0.01241 0.00455 -0.0552 0.4085 1.0000
4.750 0.8820 0.01271 0.00480 -0.0546 0.3962 1.0000
5.000 0.9066 0.01300 0.00509 -0.0540 0.3839 1.0000
5.250 0.9311 0.01325 0.00537 -0.0534 0.3713 1.0000
5.500 0.9556 0.01350 0.00566 -0.0528 0.3585 1.0000
5.750 0.9799 0.01376 0.00595 -0.0522 0.3452 1.0000
6.000 1.0039 0.01403 0.00628 -0.0515 0.3310 1.0000
6.250 1.0271 0.01429 0.00652 -0.0507 0.3133 1.0000
6.500 1.0502 0.01450 0.00678 -0.0500 0.2903 1.0000
6.750 1.0727 0.01484 0.00710 -0.0491 0.2674 1.0000
7.000 1.0945 0.01524 0.00742 -0.0483 0.2384 1.0000
7.250 1.1160 0.01575 0.00790 -0.0474 0.2151 1.0000
7.500 1.1378 0.01626 0.00838 -0.0466 0.1916 1.0000
7.750 1.1589 0.01684 0.00889 -0.0457 0.1658 1.0000
8.000 1.1790 0.01755 0.00949 -0.0447 0.1394 1.0000
8.250 1.1990 0.01830 0.01022 -0.0436 0.1174 1.0000
8.500 1.2160 0.01943 0.01109 -0.0422 0.0678 1.0000
8.750 1.2246 0.02146 0.01273 -0.0398 0.0284 1.0000
9.000 1.2405 0.02262 0.01404 -0.0381 0.0252 1.0000
9.250 1.2547 0.02388 0.01548 -0.0362 0.0233 1.0000
9.500 1.2656 0.02535 0.01717 -0.0339 0.0222 1.0000
9.750 1.2718 0.02704 0.01908 -0.0311 0.0215 1.0000
10.000 1.2770 0.02865 0.02086 -0.0283 0.0212 1.0000
10.250 1.2798 0.03018 0.02253 -0.0251 0.0209 1.0000
10.500 1.2816 0.03179 0.02428 -0.0221 0.0200 1.0000
10.750 1.2828 0.03357 0.02618 -0.0195 0.0195 1.0000
11.000 1.2838 0.03559 0.02833 -0.0171 0.0191 1.0000
11.250 1.2854 0.03782 0.03069 -0.0150 0.0189 1.0000
11.500 1.2886 0.04016 0.03317 -0.0133 0.0189 1.0000
11.750 1.2926 0.04267 0.03583 -0.0118 0.0188 1.0000
12.000 1.2963 0.04545 0.03879 -0.0104 0.0188 1.0000
12.250 1.2995 0.04831 0.04187 -0.0092 0.0191 1.0000
12.500 1.2994 0.05168 0.04546 -0.0082 0.0193 1.0000
12.750 1.2964 0.05532 0.04938 -0.0076 0.0196 1.0000
13.000 1.2907 0.05932 0.05361 -0.0075 0.0200 1.0000
13.250 1.2810 0.06396 0.05849 -0.0079 0.0203 1.0000
13.500 1.2701 0.06880 0.06355 -0.0090 0.0206 1.0000
13.750 1.2557 0.07443 0.06941 -0.0107 0.0208 1.0000
14.000 1.2406 0.08054 0.07571 -0.0128 0.0212 1.0000
14.250 1.2406 0.08440 0.07972 -0.0137 0.0218 1.0000
14.500 1.2292 0.08957 0.08506 -0.0167 0.0220 1.0000
14.750 1.2147 0.09559 0.09128 -0.0204 0.0223 1.0000
15.000 1.1966 0.10277 0.09867 -0.0251 0.0225 1.0000
15.250 1.1780 0.11057 0.10665 -0.0303 0.0227 1.0000
15.500 1.1577 0.11930 0.11555 -0.0362 0.0228 1.0000
15.750 1.1384 0.12834 0.12473 -0.0422 0.0228 1.0000
16.000 1.1177 0.13841 0.13490 -0.0490 0.0229 1.0000
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Polar data table (+)
Polar graphs
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