GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.07 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe310-il-1000000.txt Download as CSV file: xf-goe310-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3550 0.10695 0.10529 -0.0323 1.0000 0.0126
-10.000 -0.3534 0.10367 0.10203 -0.0328 1.0000 0.0126
-9.750 -0.3570 0.09962 0.09800 -0.0330 1.0000 0.0129
-9.500 -0.3539 0.09727 0.09567 -0.0328 1.0000 0.0130
-9.250 -0.3512 0.09517 0.09359 -0.0323 1.0000 0.0132
-9.000 -0.3501 0.09319 0.09163 -0.0317 1.0000 0.0134
-8.750 -0.3488 0.09067 0.08913 -0.0320 0.9997 0.0135
-8.500 -0.3341 0.08694 0.08540 -0.0362 0.9983 0.0139
-8.250 -0.3187 0.08305 0.08151 -0.0411 0.9953 0.0150
-8.000 -0.3097 0.07589 0.07436 -0.0512 0.9870 0.0162
-7.000 -0.2683 0.02634 0.02376 -0.0946 0.9484 0.0146
-6.750 -0.2550 0.02150 0.01826 -0.0942 0.9386 0.0158
-6.500 -0.2399 0.01880 0.01505 -0.0926 0.9292 0.0167
-6.250 -0.2170 0.01805 0.01423 -0.0921 0.9221 0.0172
-6.000 -0.1917 0.01777 0.01393 -0.0918 0.9148 0.0177
-5.750 -0.1686 0.01709 0.01312 -0.0910 0.9073 0.0184
-5.500 -0.1460 0.01626 0.01209 -0.0900 0.8991 0.0193
-5.250 -0.1232 0.01552 0.01113 -0.0889 0.8909 0.0202
-5.000 -0.1008 0.01481 0.01011 -0.0877 0.8825 0.0216
-4.750 -0.0784 0.01372 0.00899 -0.0868 0.8738 0.0225
-4.500 -0.0541 0.01314 0.00835 -0.0862 0.8648 0.0233
-4.250 -0.0301 0.01253 0.00763 -0.0853 0.8538 0.0241
-4.000 -0.0058 0.01193 0.00690 -0.0844 0.8417 0.0247
-3.750 0.0192 0.01166 0.00651 -0.0836 0.8277 0.0259
-3.500 0.0444 0.01189 0.00655 -0.0828 0.8109 0.0275
-3.250 0.0682 0.01115 0.00566 -0.0818 0.7912 0.0276
-3.000 0.0920 0.01058 0.00495 -0.0808 0.7682 0.0276
-2.750 0.1150 0.00990 0.00414 -0.0797 0.7456 0.0279
-2.500 0.1379 0.00929 0.00345 -0.0786 0.7249 0.0288
-2.250 0.1616 0.00900 0.00307 -0.0776 0.7062 0.0296
-2.000 0.1859 0.00878 0.00276 -0.0767 0.6897 0.0301
-1.750 0.2105 0.00860 0.00250 -0.0759 0.6749 0.0304
-1.500 0.2355 0.00844 0.00228 -0.0752 0.6618 0.0307
-1.250 0.2606 0.00830 0.00208 -0.0745 0.6500 0.0311
-1.000 0.2858 0.00819 0.00190 -0.0739 0.6390 0.0314
-0.750 0.3111 0.00810 0.00175 -0.0732 0.6288 0.0322
-0.500 0.3362 0.00802 0.00161 -0.0726 0.6158 0.0328
-0.250 0.3611 0.00798 0.00149 -0.0718 0.6013 0.0335
0.000 0.3866 0.00793 0.00139 -0.0712 0.5907 0.0344
0.250 0.4119 0.00792 0.00133 -0.0706 0.5816 0.0348
0.500 0.4379 0.00789 0.00126 -0.0701 0.5725 0.0359
0.750 0.4633 0.00790 0.00122 -0.0696 0.5616 0.0374
1.000 0.4884 0.00793 0.00119 -0.0689 0.5472 0.0402
1.250 0.5113 0.00775 0.00118 -0.0679 0.5337 0.1150
1.750 0.5607 0.00775 0.00132 -0.0666 0.5092 0.1921
2.000 0.5858 0.00780 0.00137 -0.0660 0.4951 0.2047
2.250 0.6106 0.00788 0.00141 -0.0653 0.4787 0.2132
2.500 0.6353 0.00798 0.00146 -0.0647 0.4612 0.2211
2.750 0.6589 0.00811 0.00153 -0.0639 0.4345 0.2306
3.000 0.6804 0.00837 0.00164 -0.0627 0.3901 0.2424
3.250 0.6973 0.00892 0.00189 -0.0607 0.3127 0.2650
3.500 0.7116 0.00946 0.00229 -0.0583 0.2319 0.3671
3.750 0.7184 0.00923 0.00256 -0.0543 0.1803 0.7032
4.250 0.8599 0.01041 0.00382 -0.0747 0.0568 0.9948
4.500 0.9096 0.01064 0.00404 -0.0798 0.0555 0.9985
4.750 0.9455 0.01086 0.00428 -0.0818 0.0545 1.0000
5.000 0.9665 0.01110 0.00453 -0.0805 0.0532 1.0000
5.250 0.9870 0.01137 0.00481 -0.0790 0.0515 1.0000
5.500 1.0067 0.01168 0.00514 -0.0775 0.0491 1.0000
5.750 1.0257 0.01203 0.00554 -0.0758 0.0471 1.0000
6.000 1.0467 0.01224 0.00576 -0.0745 0.0466 1.0000
6.250 1.0672 0.01247 0.00602 -0.0731 0.0459 1.0000
6.500 1.0878 0.01268 0.00625 -0.0718 0.0445 1.0000
6.750 1.1077 0.01294 0.00652 -0.0703 0.0430 1.0000
7.000 1.1272 0.01321 0.00681 -0.0687 0.0414 1.0000
7.250 1.1459 0.01352 0.00714 -0.0671 0.0396 1.0000
7.500 1.1615 0.01401 0.00767 -0.0649 0.0368 1.0000
7.750 1.1862 0.01394 0.00758 -0.0643 0.0352 1.0000
8.000 1.2086 0.01399 0.00759 -0.0634 0.0304 1.0000
8.250 1.2268 0.01429 0.00778 -0.0617 0.0216 1.0000
8.500 1.2415 0.01478 0.00822 -0.0593 0.0169 1.0000
8.750 1.2567 0.01523 0.00872 -0.0571 0.0154 1.0000
9.000 1.2706 0.01574 0.00926 -0.0546 0.0142 1.0000
9.250 1.2813 0.01633 0.00988 -0.0515 0.0128 1.0000
9.500 1.2880 0.01691 0.01052 -0.0477 0.0121 1.0000
9.750 1.2985 0.01736 0.01104 -0.0446 0.0117 1.0000
10.000 1.3084 0.01791 0.01164 -0.0416 0.0112 1.0000
10.250 1.3184 0.01851 0.01231 -0.0387 0.0108 1.0000
10.500 1.3274 0.01923 0.01307 -0.0359 0.0102 1.0000
10.750 1.3354 0.02005 0.01396 -0.0331 0.0098 1.0000
11.000 1.3402 0.02111 0.01509 -0.0300 0.0095 1.0000
11.250 1.3334 0.02297 0.01710 -0.0257 0.0090 1.0000
11.500 1.3443 0.02380 0.01800 -0.0238 0.0089 1.0000
11.750 1.3521 0.02490 0.01918 -0.0218 0.0087 1.0000
12.000 1.3592 0.02610 0.02046 -0.0198 0.0085 1.0000
12.250 1.3670 0.02731 0.02174 -0.0181 0.0082 1.0000
12.500 1.3757 0.02849 0.02298 -0.0166 0.0079 1.0000
12.750 1.3791 0.03018 0.02476 -0.0149 0.0077 1.0000
13.000 1.3850 0.03173 0.02638 -0.0135 0.0074 1.0000
13.250 1.3858 0.03381 0.02857 -0.0121 0.0074 1.0000
13.500 1.3907 0.03562 0.03044 -0.0111 0.0071 1.0000
13.750 1.3931 0.03774 0.03263 -0.0102 0.0069 1.0000
14.000 1.3906 0.04043 0.03543 -0.0093 0.0069 1.0000
14.250 1.3834 0.04371 0.03881 -0.0085 0.0066 1.0000
14.500 1.3676 0.04801 0.04327 -0.0074 0.0064 1.0000
14.750 1.3599 0.05156 0.04695 -0.0068 0.0064 1.0000
15.000 1.3636 0.05399 0.04948 -0.0070 0.0063 1.0000
15.250 1.3613 0.05715 0.05275 -0.0069 0.0063 1.0000
15.500 1.3649 0.05976 0.05545 -0.0074 0.0061 1.0000
15.750 1.3587 0.06351 0.05932 -0.0075 0.0061 1.0000
16.000 1.3553 0.06708 0.06301 -0.0080 0.0060 1.0000
16.250 1.3529 0.07061 0.06665 -0.0088 0.0059 1.0000
16.500 1.3449 0.07491 0.07108 -0.0095 0.0060 1.0000
16.750 1.3396 0.07904 0.07532 -0.0106 0.0058 1.0000
17.000 1.3288 0.08398 0.08040 -0.0118 0.0059 1.0000
17.250 1.3237 0.08836 0.08489 -0.0133 0.0057 1.0000
17.500 1.3127 0.09364 0.09030 -0.0150 0.0057 1.0000
17.750 1.2983 0.09960 0.09640 -0.0170 0.0057 1.0000
18.000 1.2910 0.10466 0.10157 -0.0191 0.0056 1.0000
18.250 1.2762 0.11109 0.10815 -0.0217 0.0056 1.0000
18.500 1.2639 0.11721 0.11439 -0.0245 0.0056 1.0000
18.750 1.2502 0.12383 0.12113 -0.0276 0.0055 1.0000
19.000 1.2310 0.13169 0.12915 -0.0314 0.0056 1.0000
19.250 1.2267 0.13683 0.13436 -0.0341 0.0054 1.0000
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