GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 622 AIRFOIL (goe622-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.63 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe622-il-1000000.txt Download as CSV file: xf-goe622-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 622 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4073 0.10737 0.10581 -0.0134 1.0000 0.0110
-10.500 -0.4078 0.10300 0.10145 -0.0145 1.0000 0.0110
-10.250 -0.4214 0.09604 0.09451 -0.0160 1.0000 0.0115
-10.000 -0.4215 0.09207 0.09055 -0.0170 1.0000 0.0116
-9.750 -0.4215 0.08813 0.08662 -0.0180 1.0000 0.0118
-9.500 -0.4228 0.08387 0.08237 -0.0192 1.0000 0.0119
-9.250 -0.4249 0.07947 0.07798 -0.0205 1.0000 0.0120
-9.000 -0.4304 0.07433 0.07285 -0.0221 1.0000 0.0121
-8.750 -0.6803 0.03277 0.03054 -0.0500 1.0000 0.0071
-8.500 -0.6808 0.02626 0.02342 -0.0494 1.0000 0.0072
-8.250 -0.6667 0.02366 0.02048 -0.0483 1.0000 0.0074
-8.000 -0.6479 0.02233 0.01895 -0.0472 1.0000 0.0076
-7.750 -0.6377 0.01841 0.01447 -0.0455 1.0000 0.0078
-7.500 -0.6215 0.01624 0.01199 -0.0440 1.0000 0.0082
-7.250 -0.6000 0.01518 0.01080 -0.0432 0.9998 0.0085
-7.000 -0.5665 0.01428 0.00978 -0.0447 0.9982 0.0088
-6.750 -0.5326 0.01346 0.00883 -0.0463 0.9964 0.0093
-6.500 -0.4985 0.01266 0.00790 -0.0479 0.9948 0.0099
-6.250 -0.4657 0.01214 0.00730 -0.0491 0.9925 0.0106
-6.000 -0.4326 0.01188 0.00699 -0.0503 0.9897 0.0110
-5.750 -0.4012 0.01039 0.00530 -0.0514 0.9870 0.0124
-5.500 -0.3672 0.00994 0.00480 -0.0528 0.9849 0.0135
-5.250 -0.3344 0.00953 0.00435 -0.0539 0.9817 0.0146
-5.000 -0.3034 0.00924 0.00401 -0.0546 0.9756 0.0156
-4.750 -0.2710 0.00862 0.00335 -0.0556 0.9709 0.0188
-4.500 -0.2408 0.00840 0.00310 -0.0561 0.9628 0.0213
-4.250 -0.2100 0.00799 0.00267 -0.0566 0.9552 0.0266
-4.000 -0.1807 0.00783 0.00249 -0.0569 0.9450 0.0304
-3.750 -0.1528 0.00753 0.00217 -0.0568 0.9342 0.0387
-3.500 -0.1252 0.00735 0.00195 -0.0566 0.9240 0.0460
-3.250 -0.0980 0.00716 0.00176 -0.0564 0.9144 0.0573
-3.000 -0.0709 0.00696 0.00165 -0.0562 0.9047 0.0815
-2.750 -0.0435 0.00686 0.00156 -0.0560 0.8958 0.0985
-2.500 -0.0160 0.00679 0.00147 -0.0558 0.8871 0.1097
-2.250 0.0117 0.00671 0.00138 -0.0557 0.8781 0.1186
-2.000 0.0391 0.00662 0.00128 -0.0555 0.8676 0.1278
-1.750 0.0664 0.00655 0.00119 -0.0553 0.8559 0.1393
-1.500 0.0936 0.00643 0.00110 -0.0551 0.8431 0.1630
-1.250 0.1206 0.00621 0.00102 -0.0549 0.8282 0.2182
-1.000 0.1470 0.00591 0.00095 -0.0547 0.8074 0.3111
-0.750 0.1723 0.00543 0.00089 -0.0544 0.7835 0.4780
-0.500 0.1973 0.00495 0.00087 -0.0539 0.7598 0.6497
-0.250 0.2213 0.00462 0.00087 -0.0530 0.7334 0.7848
0.000 0.2433 0.00443 0.00090 -0.0514 0.7047 0.8884
0.250 0.2681 0.00446 0.00092 -0.0503 0.6741 0.9549
0.500 0.3046 0.00458 0.00093 -0.0521 0.6456 0.9846
0.750 0.3445 0.00471 0.00094 -0.0549 0.6210 0.9986
1.000 0.3727 0.00484 0.00097 -0.0550 0.6006 1.0000
1.250 0.3988 0.00496 0.00099 -0.0546 0.5816 1.0000
1.500 0.4251 0.00508 0.00103 -0.0542 0.5635 1.0000
1.750 0.4517 0.00519 0.00107 -0.0539 0.5480 1.0000
2.000 0.4784 0.00530 0.00113 -0.0537 0.5327 1.0000
2.250 0.5051 0.00543 0.00118 -0.0534 0.5128 1.0000
2.500 0.5317 0.00559 0.00125 -0.0531 0.4897 1.0000
2.750 0.5583 0.00575 0.00132 -0.0529 0.4632 1.0000
3.000 0.5849 0.00593 0.00141 -0.0527 0.4352 1.0000
3.250 0.6109 0.00620 0.00152 -0.0524 0.3942 1.0000
3.500 0.6354 0.00668 0.00170 -0.0519 0.3261 1.0000
3.750 0.6605 0.00711 0.00191 -0.0515 0.2768 1.0000
4.000 0.6860 0.00748 0.00211 -0.0512 0.2366 1.0000
4.250 0.7119 0.00780 0.00230 -0.0509 0.2054 1.0000
4.500 0.7365 0.00831 0.00255 -0.0505 0.1510 1.0000
4.750 0.7619 0.00870 0.00281 -0.0502 0.1235 1.0000
5.000 0.7881 0.00899 0.00304 -0.0500 0.1100 1.0000
5.250 0.8142 0.00926 0.00327 -0.0498 0.0959 1.0000
5.500 0.8380 0.00990 0.00364 -0.0492 0.0492 1.0000
5.750 0.8612 0.01063 0.00417 -0.0485 0.0174 1.0000
6.000 0.8867 0.01103 0.00462 -0.0481 0.0142 1.0000
6.250 0.9124 0.01138 0.00503 -0.0477 0.0132 1.0000
6.500 0.9374 0.01182 0.00552 -0.0473 0.0121 1.0000
6.750 0.9620 0.01233 0.00608 -0.0467 0.0112 1.0000
7.000 0.9843 0.01317 0.00704 -0.0458 0.0101 1.0000
7.250 1.0077 0.01381 0.00776 -0.0451 0.0095 1.0000
7.500 1.0320 0.01428 0.00828 -0.0446 0.0090 1.0000
7.750 1.0552 0.01491 0.00897 -0.0439 0.0085 1.0000
8.000 1.0778 0.01560 0.00972 -0.0431 0.0081 1.0000
8.250 1.0999 0.01632 0.01050 -0.0423 0.0077 1.0000
8.500 1.1215 0.01709 0.01134 -0.0415 0.0074 1.0000
8.750 1.1418 0.01800 0.01231 -0.0405 0.0071 1.0000
9.000 1.1577 0.01952 0.01393 -0.0388 0.0067 1.0000
9.250 1.1691 0.02197 0.01654 -0.0366 0.0064 1.0000
9.500 1.1903 0.02264 0.01732 -0.0357 0.0063 1.0000
9.750 1.2091 0.02371 0.01851 -0.0345 0.0061 1.0000
10.000 1.2269 0.02485 0.01977 -0.0332 0.0058 1.0000
10.250 1.2436 0.02605 0.02112 -0.0319 0.0056 1.0000
10.500 1.2584 0.02742 0.02263 -0.0303 0.0054 1.0000
10.750 1.2703 0.02913 0.02450 -0.0285 0.0053 1.0000
11.000 1.2793 0.03105 0.02661 -0.0264 0.0052 1.0000
11.250 1.2850 0.03308 0.02883 -0.0240 0.0051 1.0000
11.500 1.2854 0.03502 0.03095 -0.0208 0.0051 1.0000
11.750 1.2809 0.03740 0.03353 -0.0177 0.0051 1.0000
12.000 1.2749 0.03995 0.03628 -0.0151 0.0050 1.0000
12.250 1.2663 0.04295 0.03947 -0.0132 0.0050 1.0000
12.500 1.2535 0.04672 0.04345 -0.0120 0.0050 1.0000
12.750 1.2413 0.05074 0.04766 -0.0119 0.0050 1.0000
13.000 1.2258 0.05568 0.05280 -0.0129 0.0050 1.0000
13.250 1.2058 0.06193 0.05926 -0.0153 0.0050 1.0000
13.500 1.1840 0.06918 0.06671 -0.0191 0.0051 1.0000
13.750 1.1629 0.07697 0.07468 -0.0237 0.0051 1.0000
14.000 1.1359 0.08656 0.08445 -0.0297 0.0052 1.0000
14.250 1.1107 0.09666 0.09470 -0.0360 0.0053 1.0000
14.500 1.0848 0.10776 0.10594 -0.0429 0.0054 1.0000
14.750 1.0565 0.12016 0.11847 -0.0501 0.0055 1.0000
15.000 1.0228 0.13469 0.13310 -0.0579 0.0057 1.0000
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