GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 200,000 Max Cl/Cd: 73.08 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe92-il-200000.txt Download as CSV file: xf-goe92-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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 -0.2635 0.09189 0.08889 -0.0248 1.0000 0.0224
-7.250 -0.2744 0.09071 0.08781 -0.0223 1.0000 0.0225
-7.000 -0.2944 0.09038 0.08757 -0.0179 1.0000 0.0226
-6.750 -0.3004 0.08868 0.08592 -0.0172 0.9991 0.0228
-6.500 -0.2699 0.08377 0.08100 -0.0256 0.9931 0.0235
-6.250 -0.2375 0.07889 0.07608 -0.0343 0.9862 0.0244
-6.000 -0.2005 0.07403 0.07117 -0.0441 0.9785 0.0256
-5.750 -0.1396 0.06920 0.06615 -0.0614 0.9712 0.0268
-5.500 -0.0956 0.06489 0.06164 -0.0707 0.9629 0.0270
-5.250 -0.0729 0.05832 0.05509 -0.0743 0.9579 0.0277
-5.000 -0.0543 0.05455 0.05135 -0.0753 0.9499 0.0289
-4.750 -0.0204 0.05068 0.04738 -0.0800 0.9429 0.0306
-4.500 0.0106 0.04723 0.04379 -0.0836 0.9321 0.0322
-4.250 0.0479 0.04427 0.04058 -0.0873 0.9213 0.0347
-4.000 0.0893 0.04310 0.03888 -0.0897 0.9102 0.0360
-3.750 0.1063 0.03748 0.03326 -0.0907 0.8995 0.0373
-3.500 0.1256 0.03494 0.03067 -0.0905 0.8864 0.0389
-3.250 0.1491 0.03279 0.02835 -0.0903 0.8727 0.0418
-3.000 0.1809 0.03104 0.02606 -0.0901 0.8588 0.0487
-2.750 0.2002 0.02842 0.02346 -0.0898 0.8436 0.0519
-2.500 0.2320 0.02938 0.02379 -0.0884 0.8264 0.0611
-2.250 0.2510 0.02480 0.01931 -0.0888 0.8081 0.0656
-2.000 0.2772 0.02336 0.01754 -0.0882 0.7878 0.0780
-1.750 0.3011 0.02185 0.01588 -0.0878 0.7641 0.0940
-1.500 0.3252 0.02066 0.01446 -0.0874 0.7370 0.1221
-0.250 0.4647 0.01575 0.00747 -0.0824 0.6025 0.0835
0.000 0.4922 0.01548 0.00683 -0.0814 0.5800 0.0739
0.250 0.5184 0.01503 0.00619 -0.0808 0.5580 0.0738
0.500 0.5443 0.01454 0.00555 -0.0801 0.5371 0.0711
0.750 0.5702 0.01424 0.00514 -0.0795 0.5167 0.0696
1.000 0.5960 0.01407 0.00484 -0.0790 0.4988 0.0694
1.250 0.6219 0.01397 0.00463 -0.0786 0.4829 0.0702
1.500 0.6481 0.01398 0.00452 -0.0783 0.4686 0.0741
1.750 0.6746 0.01399 0.00443 -0.0780 0.4560 0.0757
2.000 0.7012 0.01403 0.00436 -0.0777 0.4454 0.0793
2.250 0.7279 0.01418 0.00438 -0.0775 0.4370 0.0874
2.500 0.7565 0.01248 0.00456 -0.0778 0.4287 1.0000
2.750 0.7830 0.01277 0.00467 -0.0775 0.4215 1.0000
3.000 0.8095 0.01302 0.00478 -0.0772 0.4139 1.0000
3.250 0.8358 0.01331 0.00495 -0.0770 0.4073 1.0000
3.500 0.8622 0.01356 0.00512 -0.0768 0.4004 1.0000
3.750 0.8885 0.01390 0.00535 -0.0766 0.3949 1.0000
4.000 0.9149 0.01414 0.00560 -0.0765 0.3890 1.0000
4.250 0.9412 0.01444 0.00583 -0.0763 0.3839 1.0000
4.500 0.9676 0.01478 0.00613 -0.0762 0.3794 1.0000
4.750 0.9939 0.01506 0.00647 -0.0760 0.3748 1.0000
5.000 1.0202 0.01538 0.00677 -0.0759 0.3704 1.0000
5.250 1.0465 0.01577 0.00711 -0.0758 0.3661 1.0000
5.500 1.0723 0.01605 0.00748 -0.0756 0.3614 1.0000
5.750 1.0983 0.01636 0.00784 -0.0754 0.3568 1.0000
6.000 1.1233 0.01665 0.00814 -0.0751 0.3495 1.0000
6.250 1.1469 0.01682 0.00824 -0.0745 0.3378 1.0000
6.500 1.1705 0.01691 0.00844 -0.0740 0.3277 1.0000
6.750 1.1949 0.01719 0.00879 -0.0736 0.3206 1.0000
7.000 1.2181 0.01736 0.00897 -0.0730 0.3100 1.0000
7.250 1.2400 0.01741 0.00908 -0.0721 0.2944 1.0000
7.500 1.2628 0.01748 0.00927 -0.0715 0.2789 1.0000
7.750 1.2854 0.01759 0.00943 -0.0708 0.2546 1.0000
8.000 1.3049 0.01811 0.00976 -0.0698 0.1991 1.0000
8.250 1.3133 0.01999 0.01107 -0.0677 0.1277 1.0000
8.500 1.3245 0.02157 0.01239 -0.0658 0.0736 1.0000
8.750 1.3282 0.02369 0.01424 -0.0630 0.0304 1.0000
9.000 1.3405 0.02488 0.01555 -0.0610 0.0260 1.0000
9.250 1.3528 0.02601 0.01687 -0.0591 0.0243 1.0000
9.500 1.3620 0.02716 0.01826 -0.0567 0.0236 1.0000
9.750 1.3685 0.02851 0.01981 -0.0542 0.0230 1.0000
10.000 1.3724 0.03009 0.02159 -0.0518 0.0226 1.0000
10.250 1.3736 0.03198 0.02369 -0.0496 0.0223 1.0000
10.500 1.3724 0.03421 0.02611 -0.0476 0.0221 1.0000
10.750 1.3687 0.03685 0.02893 -0.0461 0.0220 1.0000
11.000 1.3629 0.03991 0.03217 -0.0450 0.0217 1.0000
11.250 1.3558 0.04340 0.03581 -0.0445 0.0215 1.0000
11.500 1.3477 0.04732 0.03987 -0.0446 0.0211 1.0000
11.750 1.3391 0.05155 0.04424 -0.0451 0.0208 1.0000
12.000 1.3307 0.05588 0.04867 -0.0457 0.0204 1.0000
12.250 1.3231 0.06007 0.05297 -0.0461 0.0201 1.0000
12.500 1.3180 0.06383 0.05681 -0.0462 0.0200 1.0000
12.750 1.3155 0.06708 0.06013 -0.0459 0.0200 1.0000
13.000 1.3166 0.06976 0.06288 -0.0450 0.0202 1.0000
13.250 1.3227 0.07162 0.06479 -0.0434 0.0204 1.0000
13.500 1.3356 0.07247 0.06569 -0.0407 0.0211 1.0000
13.750 1.3532 0.07299 0.06629 -0.0374 0.0223 1.0000
14.000 1.0834 0.09116 0.08540 -0.0356 0.0211 1.0000
14.250 1.0877 0.09275 0.08702 -0.0343 0.0209 1.0000
14.500 1.0992 0.09306 0.08736 -0.0321 0.0211 1.0000
14.750 1.1164 0.09254 0.08688 -0.0290 0.0216 1.0000
15.000 1.1356 0.09178 0.08621 -0.0253 0.0227 1.0000
15.250 1.1940 0.08700 0.08141 -0.0175 0.0256 1.0000
15.500 1.1742 0.09068 0.08532 -0.0184 0.0262 1.0000
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Polar data table (+)
Polar graphs
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