GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 200,000 Max Cl/Cd: 75.66 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe402-il-200000.txt Download as CSV file: xf-goe402-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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 -0.2783 0.09227 0.08901 -0.0211 1.0000 0.0249
-7.250 -0.2787 0.09019 0.08699 -0.0207 1.0000 0.0253
-7.000 -0.2806 0.08823 0.08511 -0.0201 1.0000 0.0258
-6.750 -0.2782 0.08602 0.08296 -0.0208 1.0000 0.0263
-6.500 -0.2749 0.08406 0.08107 -0.0223 1.0000 0.0269
-6.250 -0.2709 0.08239 0.07946 -0.0245 1.0000 0.0272
-6.000 -0.2715 0.08131 0.07846 -0.0258 0.9999 0.0274
-5.750 -0.2152 0.07660 0.07362 -0.0411 0.9912 0.0277
-5.500 -0.1753 0.07038 0.06734 -0.0500 0.9839 0.0280
-5.250 -0.1577 0.06472 0.06173 -0.0509 0.9750 0.0287
-5.000 -0.1254 0.06030 0.05727 -0.0556 0.9652 0.0298
-4.750 -0.0837 0.05598 0.05286 -0.0630 0.9561 0.0319
-4.500 -0.0282 0.05231 0.04898 -0.0731 0.9409 0.0359
-4.250 0.0294 0.04949 0.04576 -0.0817 0.9225 0.0367
-4.000 0.0540 0.04333 0.03960 -0.0850 0.9046 0.0378
-3.750 0.0827 0.03998 0.03615 -0.0874 0.8843 0.0394
-3.500 0.1134 0.03728 0.03325 -0.0896 0.8616 0.0420
-3.250 0.1609 0.03663 0.03189 -0.0922 0.8420 0.0477
-3.000 0.1775 0.03196 0.02724 -0.0929 0.8250 0.0498
-2.750 0.2006 0.03003 0.02516 -0.0929 0.8088 0.0528
-2.500 0.2357 0.02887 0.02334 -0.0933 0.7947 0.0606
-2.250 0.2555 0.02612 0.02062 -0.0933 0.7811 0.0638
-2.000 0.2832 0.02473 0.01884 -0.0932 0.7680 0.0755
-1.750 0.3087 0.02358 0.01745 -0.0930 0.7549 0.0893
-1.500 0.3335 0.02232 0.01603 -0.0928 0.7424 0.1038
-1.250 0.3575 0.02105 0.01468 -0.0926 0.7306 0.1203
0.000 0.4991 0.01558 0.00759 -0.0888 0.6734 0.0854
0.250 0.5265 0.01468 0.00643 -0.0880 0.6625 0.0768
0.500 0.5534 0.01448 0.00605 -0.0872 0.6504 0.0739
0.750 0.5795 0.01397 0.00548 -0.0865 0.6373 0.0732
1.000 0.6050 0.01336 0.00486 -0.0859 0.6238 0.0755
1.250 0.6305 0.01300 0.00450 -0.0851 0.6097 0.0770
1.500 0.6559 0.01276 0.00422 -0.0844 0.5951 0.0779
1.750 0.6813 0.01260 0.00402 -0.0837 0.5800 0.0802
2.000 0.7067 0.01254 0.00386 -0.0830 0.5639 0.0840
2.250 0.7319 0.01252 0.00375 -0.0823 0.5463 0.0911
2.500 0.7556 0.01206 0.00383 -0.0816 0.5276 0.3527
2.750 0.7904 0.01107 0.00380 -0.0829 0.5076 1.0000
3.000 0.8153 0.01132 0.00386 -0.0822 0.4903 1.0000
3.250 0.8402 0.01158 0.00397 -0.0815 0.4739 1.0000
3.500 0.8653 0.01184 0.00411 -0.0810 0.4592 1.0000
3.750 0.8904 0.01213 0.00427 -0.0804 0.4465 1.0000
4.000 0.9157 0.01239 0.00450 -0.0799 0.4349 1.0000
4.250 0.9411 0.01268 0.00474 -0.0795 0.4250 1.0000
4.500 0.9663 0.01301 0.00497 -0.0790 0.4167 1.0000
4.750 0.9919 0.01328 0.00526 -0.0786 0.4082 1.0000
5.000 1.0173 0.01363 0.00557 -0.0782 0.4014 1.0000
5.250 1.0426 0.01392 0.00589 -0.0778 0.3939 1.0000
5.500 1.0681 0.01431 0.00622 -0.0774 0.3880 1.0000
5.750 1.0934 0.01461 0.00660 -0.0770 0.3814 1.0000
6.000 1.1187 0.01499 0.00698 -0.0766 0.3756 1.0000
6.250 1.1437 0.01533 0.00741 -0.0762 0.3694 1.0000
6.500 1.1687 0.01567 0.00779 -0.0758 0.3629 1.0000
6.750 1.1935 0.01607 0.00824 -0.0753 0.3569 1.0000
7.000 1.2182 0.01641 0.00871 -0.0748 0.3506 1.0000
7.250 1.2423 0.01679 0.00914 -0.0743 0.3430 1.0000
7.500 1.2647 0.01707 0.00941 -0.0735 0.3308 1.0000
7.750 1.2865 0.01726 0.00974 -0.0725 0.3186 1.0000
8.000 1.3081 0.01748 0.01011 -0.0715 0.3061 1.0000
8.250 1.3285 0.01767 0.01038 -0.0704 0.2899 1.0000
8.500 1.3489 0.01791 0.01070 -0.0693 0.2731 1.0000
8.750 1.3694 0.01810 0.01105 -0.0681 0.2483 1.0000
9.000 1.3831 0.01887 0.01155 -0.0662 0.1791 1.0000
9.250 1.3782 0.02165 0.01360 -0.0623 0.0814 1.0000
9.500 1.3713 0.02442 0.01598 -0.0580 0.0416 1.0000
9.750 1.3778 0.02583 0.01754 -0.0552 0.0357 1.0000
10.000 1.3733 0.02766 0.01947 -0.0510 0.0320 1.0000
10.250 1.3759 0.02907 0.02103 -0.0481 0.0301 1.0000
10.500 1.3754 0.03079 0.02288 -0.0452 0.0284 1.0000
10.750 1.3730 0.03281 0.02504 -0.0428 0.0273 1.0000
11.000 1.3692 0.03520 0.02754 -0.0409 0.0264 1.0000
11.250 1.3643 0.03796 0.03041 -0.0396 0.0256 1.0000
11.500 1.3582 0.04110 0.03364 -0.0386 0.0250 1.0000
11.750 1.3517 0.04446 0.03707 -0.0376 0.0243 1.0000
12.000 1.3484 0.04766 0.04031 -0.0362 0.0236 1.0000
12.250 1.3530 0.05005 0.04286 -0.0355 0.0231 1.0000
12.500 1.3572 0.05253 0.04549 -0.0350 0.0223 1.0000
12.750 1.3614 0.05507 0.04815 -0.0344 0.0215 1.0000
13.000 1.3672 0.05761 0.05082 -0.0335 0.0210 1.0000
13.250 1.3735 0.06029 0.05365 -0.0326 0.0206 1.0000
13.500 1.3784 0.06323 0.05677 -0.0319 0.0203 1.0000
13.750 1.3812 0.06655 0.06029 -0.0314 0.0201 1.0000
14.000 1.3815 0.07028 0.06425 -0.0313 0.0201 1.0000
14.250 1.3780 0.07454 0.06874 -0.0316 0.0202 1.0000
14.500 1.3704 0.07938 0.07385 -0.0324 0.0203 1.0000
14.750 1.3596 0.08469 0.07941 -0.0338 0.0205 1.0000
15.000 1.3465 0.09048 0.08545 -0.0358 0.0208 1.0000
15.250 1.3316 0.09671 0.09192 -0.0384 0.0210 1.0000
15.500 1.3153 0.10341 0.09884 -0.0416 0.0213 1.0000
15.750 1.2985 0.11051 0.10615 -0.0453 0.0215 1.0000
16.000 1.2813 0.11803 0.11387 -0.0496 0.0217 1.0000
16.250 1.2638 0.12598 0.12201 -0.0545 0.0220 1.0000
16.500 1.2456 0.13445 0.13064 -0.0598 0.0222 1.0000
16.750 1.2273 0.14341 0.13976 -0.0657 0.0225 1.0000
17.000 1.2090 0.15280 0.14929 -0.0719 0.0228 1.0000
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Polar data table (+)
Polar graphs
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