GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.24 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe122-il-1000000.txt Download as CSV file: xf-goe122-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3406 0.08872 0.08728 -0.0076 1.0000 0.0116
-8.500 -0.3368 0.08532 0.08389 -0.0086 1.0000 0.0118
-8.250 -0.4448 0.09374 0.09223 -0.0005 1.0000 0.0113
-8.000 -0.4378 0.09088 0.08938 -0.0019 1.0000 0.0114
-7.750 -0.4312 0.08790 0.08643 -0.0037 1.0000 0.0116
-7.500 -0.4237 0.08465 0.08319 -0.0064 1.0000 0.0118
-7.250 -0.4119 0.08097 0.07952 -0.0105 1.0000 0.0120
-7.000 -0.3982 0.07709 0.07565 -0.0150 1.0000 0.0124
-6.750 -0.3822 0.07293 0.07148 -0.0200 1.0000 0.0131
-6.500 -0.3434 0.06459 0.06305 -0.0346 0.9713 0.0142
-6.250 -0.3182 0.05908 0.05742 -0.0407 0.9428 0.0143
-6.000 -0.2735 0.03786 0.03610 -0.0427 0.8902 0.0146
-5.750 -0.2567 0.03506 0.03323 -0.0440 0.8798 0.0149
-5.500 -0.2375 0.03189 0.02998 -0.0460 0.8700 0.0152
-5.250 -0.2370 0.04411 0.04198 -0.0509 0.8870 0.0156
-4.250 -0.1190 0.00937 0.00616 -0.0564 0.8240 0.0190
-4.000 -0.0951 0.00947 0.00627 -0.0564 0.8091 0.0199
-3.750 -0.0656 0.00895 0.00544 -0.0558 0.7945 0.0232
-3.500 -0.0404 0.00712 0.00323 -0.0557 0.7793 0.0233
-3.250 -0.0181 0.01584 0.01122 -0.0579 0.7939 0.0241
-3.000 0.0082 0.01529 0.01066 -0.0580 0.7748 0.0251
-2.750 0.0352 0.01504 0.01030 -0.0580 0.7538 0.0270
-2.500 0.0641 0.01610 0.01120 -0.0575 0.7324 0.0299
-2.250 0.0918 0.01514 0.00996 -0.0573 0.7094 0.0300
-2.000 0.1186 0.01203 0.00647 -0.0574 0.6878 0.0319
-1.750 0.1461 0.01159 0.00597 -0.0574 0.6664 0.0336
-1.500 0.1741 0.01124 0.00548 -0.0573 0.6487 0.0359
-1.250 0.2027 0.01002 0.00398 -0.0569 0.6332 0.0317
-1.000 0.2309 0.00980 0.00364 -0.0568 0.6158 0.0308
-0.750 0.2587 0.00927 0.00303 -0.0567 0.5979 0.0311
-0.500 0.2866 0.00886 0.00255 -0.0566 0.5804 0.0314
-0.250 0.3145 0.00857 0.00219 -0.0565 0.5614 0.0318
0.000 0.3424 0.00839 0.00193 -0.0565 0.5394 0.0323
0.250 0.3703 0.00830 0.00173 -0.0565 0.5139 0.0327
0.500 0.3982 0.00825 0.00158 -0.0565 0.4878 0.0331
0.750 0.4262 0.00823 0.00146 -0.0565 0.4660 0.0336
1.000 0.4542 0.00824 0.00139 -0.0565 0.4477 0.0347
1.250 0.4822 0.00824 0.00132 -0.0565 0.4330 0.0354
1.500 0.5103 0.00825 0.00129 -0.0565 0.4217 0.0367
1.750 0.5383 0.00830 0.00127 -0.0565 0.4085 0.0381
2.000 0.5663 0.00837 0.00127 -0.0565 0.3946 0.0396
2.250 0.5944 0.00841 0.00129 -0.0565 0.3850 0.0446
2.500 0.6179 0.00672 0.00154 -0.0565 0.3777 0.8365
2.750 0.6466 0.00651 0.00157 -0.0564 0.3683 1.0000
3.000 0.6746 0.00661 0.00163 -0.0564 0.3600 1.0000
3.250 0.7024 0.00675 0.00171 -0.0564 0.3488 1.0000
3.500 0.7301 0.00690 0.00180 -0.0564 0.3373 1.0000
3.750 0.7578 0.00705 0.00189 -0.0564 0.3236 1.0000
4.000 0.7854 0.00720 0.00199 -0.0564 0.3107 1.0000
4.250 0.8128 0.00739 0.00212 -0.0564 0.2946 1.0000
4.500 0.8400 0.00762 0.00226 -0.0563 0.2713 1.0000
4.750 0.8659 0.00809 0.00249 -0.0562 0.2228 1.0000
5.000 0.8906 0.00878 0.00288 -0.0560 0.1684 1.0000
5.250 0.9169 0.00917 0.00317 -0.0559 0.1464 1.0000
5.500 0.9394 0.01027 0.00379 -0.0555 0.0569 1.0000
5.750 0.9649 0.01077 0.00421 -0.0552 0.0399 1.0000
6.000 0.9911 0.01114 0.00458 -0.0550 0.0351 1.0000
6.250 1.0174 0.01146 0.00495 -0.0548 0.0331 1.0000
6.500 1.0436 0.01176 0.00528 -0.0547 0.0320 1.0000
6.750 1.0696 0.01210 0.00566 -0.0545 0.0304 1.0000
7.000 1.0951 0.01249 0.00609 -0.0543 0.0285 1.0000
7.250 1.1196 0.01308 0.00673 -0.0539 0.0260 1.0000
7.500 1.1440 0.01362 0.00734 -0.0535 0.0244 1.0000
7.750 1.1700 0.01386 0.00760 -0.0533 0.0233 1.0000
8.000 1.1952 0.01420 0.00797 -0.0531 0.0217 1.0000
8.250 1.2200 0.01460 0.00837 -0.0528 0.0202 1.0000
8.500 1.2411 0.01555 0.00940 -0.0521 0.0181 1.0000
8.750 1.2669 0.01574 0.00961 -0.0519 0.0173 1.0000
9.000 1.2918 0.01604 0.00992 -0.0517 0.0160 1.0000
9.250 1.3162 0.01640 0.01028 -0.0514 0.0149 1.0000
9.500 1.3354 0.01744 0.01140 -0.0504 0.0134 1.0000
9.750 1.3588 0.01786 0.01187 -0.0500 0.0128 1.0000
10.000 1.3812 0.01839 0.01245 -0.0494 0.0121 1.0000
10.250 1.4032 0.01893 0.01303 -0.0488 0.0114 1.0000
10.500 1.4241 0.01955 0.01367 -0.0482 0.0107 1.0000
10.750 1.4361 0.02108 0.01532 -0.0464 0.0098 1.0000
11.000 1.4563 0.02168 0.01598 -0.0456 0.0095 1.0000
11.250 1.4738 0.02248 0.01687 -0.0445 0.0091 1.0000
11.500 1.4897 0.02336 0.01784 -0.0433 0.0087 1.0000
11.750 1.5044 0.02427 0.01882 -0.0420 0.0084 1.0000
12.000 1.5169 0.02520 0.01983 -0.0404 0.0081 1.0000
12.250 1.5244 0.02629 0.02098 -0.0381 0.0078 1.0000
12.500 1.5268 0.02784 0.02262 -0.0358 0.0075 1.0000
12.750 1.5219 0.03022 0.02514 -0.0336 0.0073 1.0000
13.000 1.5083 0.03380 0.02891 -0.0317 0.0071 1.0000
13.250 1.5092 0.03625 0.03149 -0.0311 0.0070 1.0000
13.500 1.5114 0.03874 0.03410 -0.0309 0.0069 1.0000
13.750 1.5124 0.04152 0.03700 -0.0310 0.0068 1.0000
14.000 1.5110 0.04475 0.04036 -0.0313 0.0067 1.0000
14.250 1.5087 0.04821 0.04395 -0.0320 0.0066 1.0000
14.500 1.5054 0.05193 0.04778 -0.0329 0.0065 1.0000
14.750 1.5004 0.05594 0.05192 -0.0339 0.0064 1.0000
15.000 1.4944 0.06017 0.05626 -0.0351 0.0063 1.0000
15.250 1.4865 0.06476 0.06098 -0.0366 0.0062 1.0000
15.500 1.4775 0.06957 0.06591 -0.0382 0.0061 1.0000
15.750 1.4683 0.07458 0.07103 -0.0400 0.0060 1.0000
16.000 1.4579 0.07991 0.07648 -0.0419 0.0059 1.0000
16.250 1.4475 0.08530 0.08198 -0.0440 0.0059 1.0000
16.500 1.4359 0.09101 0.08780 -0.0463 0.0058 1.0000
16.750 1.4237 0.09692 0.09383 -0.0486 0.0058 1.0000
17.000 1.4114 0.10290 0.09992 -0.0511 0.0057 1.0000
17.250 1.3988 0.10910 0.10622 -0.0538 0.0057 1.0000
17.500 1.3863 0.11540 0.11263 -0.0566 0.0056 1.0000
17.750 1.3723 0.12204 0.11938 -0.0596 0.0056 1.0000
18.000 1.3591 0.12872 0.12617 -0.0628 0.0056 1.0000
18.250 1.3458 0.13559 0.13316 -0.0662 0.0055 1.0000
18.500 1.3332 0.14252 0.14019 -0.0698 0.0055 1.0000
18.750 1.3194 0.14985 0.14763 -0.0738 0.0055 1.0000
19.000 1.3049 0.15764 0.15554 -0.0781 0.0055 1.0000
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Polar data table (+)
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