GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.08 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe632-il-1000000.txt Download as CSV file: xf-goe632-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3528 0.10310 0.10140 -0.0448 1.0000 0.0254
-11.250 -0.5211 0.03402 0.03206 -0.0859 0.9902 0.0248
-11.000 -0.5896 0.02462 0.02214 -0.0860 0.9710 0.0247
-10.750 -0.6539 0.03283 0.02987 -0.0794 0.9637 0.0248
-10.500 -0.6572 0.02604 0.02236 -0.0798 0.9492 0.0253
-10.250 -0.6250 0.02386 0.01997 -0.0826 0.9362 0.0255
-10.000 -0.5919 0.02270 0.01865 -0.0848 0.9159 0.0258
-9.500 -0.5492 0.02128 0.01688 -0.0832 0.8680 0.0264
-9.250 -0.5332 0.02063 0.01607 -0.0812 0.8511 0.0266
-9.000 -0.5167 0.02001 0.01530 -0.0791 0.8379 0.0270
-8.750 -0.4999 0.01931 0.01445 -0.0772 0.8265 0.0273
-8.500 -0.4828 0.01852 0.01349 -0.0752 0.8164 0.0276
-8.250 -0.4647 0.01773 0.01252 -0.0734 0.8066 0.0278
-8.000 -0.4454 0.01696 0.01160 -0.0718 0.7976 0.0281
-7.750 -0.4252 0.01630 0.01078 -0.0704 0.7883 0.0284
-7.500 -0.4037 0.01575 0.01012 -0.0691 0.7790 0.0286
-7.250 -0.3820 0.01529 0.00953 -0.0678 0.7693 0.0288
-7.000 -0.3595 0.01488 0.00903 -0.0667 0.7588 0.0290
-6.750 -0.3368 0.01451 0.00856 -0.0656 0.7481 0.0291
-6.500 -0.3149 0.01328 0.00718 -0.0646 0.7369 0.0298
-6.250 -0.2917 0.01282 0.00669 -0.0637 0.7257 0.0304
-6.000 -0.2686 0.01249 0.00630 -0.0627 0.7146 0.0307
-5.500 -0.2217 0.01188 0.00556 -0.0607 0.6926 0.0315
-5.250 -0.1982 0.01160 0.00522 -0.0598 0.6831 0.0319
-5.000 -0.1744 0.01134 0.00489 -0.0589 0.6739 0.0323
-4.750 -0.1506 0.01109 0.00458 -0.0579 0.6660 0.0328
-4.500 -0.1265 0.01087 0.00431 -0.0571 0.6582 0.0332
-4.250 -0.1026 0.01069 0.00407 -0.0562 0.6513 0.0336
-4.000 -0.0777 0.01052 0.00387 -0.0555 0.6450 0.0340
-3.750 -0.0552 0.01017 0.00346 -0.0543 0.6386 0.0348
-3.500 -0.0312 0.00994 0.00322 -0.0534 0.6332 0.0358
-3.250 -0.0063 0.00979 0.00306 -0.0527 0.6277 0.0368
-3.000 0.0183 0.00966 0.00290 -0.0519 0.6225 0.0377
-2.750 0.0430 0.00956 0.00276 -0.0512 0.6173 0.0387
-2.500 0.0685 0.00944 0.00263 -0.0506 0.6125 0.0396
-2.250 0.0928 0.00926 0.00244 -0.0497 0.6077 0.0417
-2.000 0.1173 0.00918 0.00235 -0.0490 0.6026 0.0441
-1.750 0.1427 0.00906 0.00224 -0.0483 0.5981 0.0476
-1.500 0.1679 0.00897 0.00217 -0.0477 0.5932 0.0536
-1.250 0.1926 0.00889 0.00212 -0.0469 0.5882 0.0636
-1.000 0.2175 0.00885 0.00209 -0.0463 0.5835 0.0717
-0.750 0.2428 0.00875 0.00203 -0.0457 0.5790 0.0791
-0.500 0.2680 0.00870 0.00197 -0.0450 0.5738 0.0843
0.000 0.3159 0.00850 0.00188 -0.0433 0.5614 0.1183
0.250 0.3339 0.00811 0.00183 -0.0413 0.5551 0.2403
0.500 0.3504 0.00774 0.00183 -0.0390 0.5476 0.3734
0.750 0.3691 0.00750 0.00182 -0.0371 0.5404 0.4545
1.000 0.3556 0.00649 0.00170 -0.0282 0.5343 0.7430
1.250 0.4137 0.00625 0.00200 -0.0346 0.5256 0.9179
1.500 0.4578 0.00655 0.00226 -0.0380 0.5165 0.9390
1.750 0.4956 0.00680 0.00247 -0.0400 0.5065 0.9451
2.000 0.5423 0.00720 0.00280 -0.0439 0.4937 0.9488
2.250 0.5716 0.00741 0.00294 -0.0441 0.4830 0.9527
2.500 0.5915 0.00754 0.00302 -0.0423 0.4727 0.9572
2.750 0.6310 0.00776 0.00318 -0.0449 0.4623 0.9581
3.000 0.6684 0.00800 0.00335 -0.0470 0.4508 0.9593
3.250 0.7034 0.00821 0.00349 -0.0487 0.4397 0.9605
3.500 0.7393 0.00841 0.00365 -0.0505 0.4305 0.9623
3.750 0.7696 0.00861 0.00379 -0.0511 0.4210 0.9645
4.000 0.7857 0.00878 0.00395 -0.0485 0.4133 0.9702
4.250 0.8217 0.00896 0.00408 -0.0505 0.4036 0.9709
4.500 0.8545 0.00910 0.00418 -0.0518 0.3934 0.9717
4.750 0.8859 0.00924 0.00428 -0.0527 0.3851 0.9726
5.000 0.9171 0.00941 0.00440 -0.0537 0.3753 0.9736
5.250 0.9485 0.00954 0.00452 -0.0546 0.3676 0.9749
5.500 0.9777 0.00973 0.00467 -0.0552 0.3581 0.9766
5.750 1.0061 0.00989 0.00482 -0.0555 0.3501 0.9789
6.000 1.0244 0.01015 0.00503 -0.0537 0.3406 0.9828
6.250 1.0561 0.01028 0.00514 -0.0548 0.3291 0.9834
6.500 1.0856 0.01049 0.00528 -0.0556 0.3142 0.9843
6.750 1.1137 0.01070 0.00544 -0.0560 0.2999 0.9852
7.000 1.1393 0.01104 0.00566 -0.0560 0.2783 0.9866
7.250 1.1611 0.01154 0.00599 -0.0554 0.2428 0.9885
7.500 1.1704 0.01263 0.00671 -0.0527 0.1800 0.9921
7.750 1.1900 0.01322 0.00717 -0.0517 0.1592 0.9941
8.000 1.2151 0.01361 0.00750 -0.0518 0.1464 0.9954
8.250 1.2405 0.01391 0.00778 -0.0519 0.1362 0.9968
8.500 1.2621 0.01434 0.00812 -0.0514 0.1203 0.9986
8.750 1.2764 0.01485 0.00851 -0.0495 0.1029 1.0000
9.000 1.2725 0.01520 0.00884 -0.0436 0.0972 1.0000
9.250 1.2734 0.01555 0.00920 -0.0388 0.0932 1.0000
9.500 1.2772 0.01591 0.00959 -0.0347 0.0915 1.0000
9.750 1.2814 0.01633 0.01002 -0.0307 0.0896 1.0000
10.000 1.2852 0.01683 0.01054 -0.0269 0.0876 1.0000
10.250 1.2911 0.01733 0.01107 -0.0235 0.0864 1.0000
10.500 1.2952 0.01798 0.01173 -0.0200 0.0839 1.0000
10.750 1.3002 0.01866 0.01245 -0.0168 0.0820 1.0000
11.000 1.3099 0.01921 0.01305 -0.0145 0.0816 1.0000
11.250 1.3194 0.01982 0.01370 -0.0122 0.0806 1.0000
11.500 1.3282 0.02052 0.01445 -0.0099 0.0791 1.0000
11.750 1.3361 0.02132 0.01529 -0.0077 0.0779 1.0000
12.000 1.3432 0.02224 0.01624 -0.0056 0.0762 1.0000
12.250 1.3488 0.02330 0.01732 -0.0034 0.0738 1.0000
12.500 1.3527 0.02456 0.01861 -0.0012 0.0716 1.0000
12.750 1.3655 0.02527 0.01938 0.0000 0.0704 1.0000
13.000 1.3771 0.02609 0.02024 0.0013 0.0677 1.0000
13.250 1.3827 0.02737 0.02150 0.0029 0.0634 1.0000
13.500 1.3901 0.02857 0.02272 0.0043 0.0591 1.0000
13.750 1.3763 0.03145 0.02540 0.0069 0.0362 1.0000
14.000 1.3534 0.03531 0.02921 0.0095 0.0215 1.0000
14.250 1.3539 0.03738 0.03132 0.0106 0.0199 1.0000
14.500 1.3510 0.03981 0.03379 0.0118 0.0180 1.0000
14.750 1.3522 0.04194 0.03599 0.0127 0.0173 1.0000
15.000 1.3525 0.04423 0.03834 0.0135 0.0164 1.0000
15.250 1.3541 0.04643 0.04060 0.0141 0.0161 1.0000
15.500 1.3525 0.04900 0.04323 0.0148 0.0155 1.0000
15.750 1.3478 0.05197 0.04627 0.0153 0.0147 1.0000
16.000 1.3491 0.05436 0.04872 0.0157 0.0145 1.0000
16.250 1.3488 0.05699 0.05143 0.0159 0.0142 1.0000
16.500 1.3486 0.05963 0.05414 0.0161 0.0140 1.0000
16.750 1.3483 0.06233 0.05692 0.0162 0.0136 1.0000
17.000 1.3460 0.06535 0.06001 0.0162 0.0134 1.0000
17.250 1.3420 0.06861 0.06334 0.0161 0.0129 1.0000
17.500 1.3390 0.07179 0.06659 0.0159 0.0129 1.0000
17.750 1.3333 0.07537 0.07025 0.0155 0.0126 1.0000
18.000 1.3264 0.07918 0.07414 0.0150 0.0123 1.0000
18.250 1.3140 0.08381 0.07887 0.0143 0.0120 1.0000
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