MH33 (mh33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.65 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh33-il-1000000-n5.txt Download as CSV file: xf-mh33-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH33
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5642 0.08051 0.07891 -0.0160 1.0000 0.0015
-8.750 -0.5684 0.07593 0.07436 -0.0188 1.0000 0.0014
-8.500 -0.5785 0.07066 0.06912 -0.0227 1.0000 0.0014
-8.250 -0.5917 0.06465 0.06311 -0.0279 1.0000 0.0014
-8.000 -0.5998 0.05741 0.05579 -0.0323 1.0000 0.0014
-7.750 -0.6088 0.04974 0.04797 -0.0340 1.0000 0.0014
-7.500 -0.6179 0.04209 0.04007 -0.0333 1.0000 0.0013
-7.250 -0.6369 0.02879 0.02608 -0.0301 0.9989 0.0014
-7.000 -0.6178 0.02237 0.01901 -0.0307 0.9957 0.0017
-6.750 -0.5908 0.01995 0.01624 -0.0314 0.9940 0.0018
-6.500 -0.5638 0.01874 0.01484 -0.0317 0.9918 0.0019
-6.250 -0.5390 0.01608 0.01175 -0.0317 0.9891 0.0020
-6.000 -0.5119 0.01418 0.00956 -0.0320 0.9869 0.0023
-5.750 -0.4821 0.01314 0.00837 -0.0327 0.9852 0.0024
-5.500 -0.4513 0.01231 0.00743 -0.0336 0.9837 0.0025
-5.250 -0.4201 0.01152 0.00654 -0.0345 0.9822 0.0027
-5.000 -0.3910 0.01101 0.00597 -0.0349 0.9793 0.0029
-4.750 -0.3628 0.01054 0.00541 -0.0350 0.9751 0.0033
-4.500 -0.3338 0.00992 0.00471 -0.0353 0.9715 0.0035
-4.250 -0.3038 0.00928 0.00397 -0.0357 0.9684 0.0036
-4.000 -0.2785 0.00877 0.00337 -0.0351 0.9623 0.0036
-3.750 -0.2506 0.00832 0.00283 -0.0350 0.9570 0.0036
-3.500 -0.2236 0.00800 0.00242 -0.0347 0.9507 0.0036
-3.250 -0.1965 0.00773 0.00209 -0.0343 0.9435 0.0038
-3.000 -0.1698 0.00753 0.00180 -0.0340 0.9353 0.0040
-2.750 -0.1428 0.00736 0.00157 -0.0336 0.9263 0.0055
-2.500 -0.1174 0.00693 0.00132 -0.0331 0.9152 0.0522
-2.250 -0.0916 0.00663 0.00116 -0.0327 0.9019 0.0980
-2.000 -0.0666 0.00621 0.00101 -0.0322 0.8862 0.1846
-1.750 -0.0416 0.00585 0.00089 -0.0317 0.8669 0.2690
-1.500 -0.0160 0.00569 0.00079 -0.0312 0.8432 0.3179
-1.250 0.0094 0.00557 0.00071 -0.0307 0.8143 0.3673
-1.000 0.0346 0.00549 0.00065 -0.0301 0.7816 0.4169
-0.750 0.0599 0.00542 0.00061 -0.0296 0.7473 0.4700
-0.500 0.0849 0.00534 0.00057 -0.0291 0.7118 0.5321
-0.250 0.1099 0.00527 0.00056 -0.0285 0.6750 0.5948
0.000 0.1349 0.00523 0.00057 -0.0280 0.6374 0.6514
0.250 0.1597 0.00520 0.00058 -0.0274 0.5990 0.7115
0.500 0.1841 0.00516 0.00062 -0.0266 0.5614 0.7731
0.750 0.2074 0.00512 0.00068 -0.0256 0.5248 0.8408
1.000 0.2305 0.00517 0.00077 -0.0244 0.4887 0.8954
1.250 0.2548 0.00532 0.00085 -0.0235 0.4526 0.9255
1.500 0.2801 0.00551 0.00092 -0.0228 0.4151 0.9434
1.750 0.3063 0.00570 0.00100 -0.0225 0.3785 0.9561
2.000 0.3340 0.00591 0.00109 -0.0225 0.3438 0.9658
2.250 0.3637 0.00610 0.00117 -0.0229 0.3123 0.9732
2.500 0.3924 0.00632 0.00127 -0.0232 0.2804 0.9809
2.750 0.4258 0.00656 0.00137 -0.0246 0.2461 0.9849
3.000 0.4586 0.00682 0.00152 -0.0258 0.2108 0.9885
3.250 0.4906 0.00707 0.00166 -0.0269 0.1818 0.9920
3.500 0.5229 0.00735 0.00181 -0.0281 0.1503 0.9950
3.750 0.5560 0.00761 0.00198 -0.0295 0.1261 0.9978
4.000 0.5872 0.00795 0.00217 -0.0304 0.0953 1.0000
4.250 0.6100 0.00822 0.00239 -0.0295 0.0753 1.0000
4.500 0.6329 0.00850 0.00259 -0.0286 0.0593 1.0000
4.750 0.6558 0.00881 0.00283 -0.0277 0.0419 1.0000
5.000 0.6780 0.00924 0.00312 -0.0267 0.0211 1.0000
5.250 0.7012 0.00956 0.00340 -0.0258 0.0128 1.0000
5.500 0.7253 0.00982 0.00366 -0.0251 0.0101 1.0000
5.750 0.7495 0.01010 0.00394 -0.0245 0.0080 1.0000
6.000 0.7741 0.01037 0.00427 -0.0239 0.0063 1.0000
6.250 0.7979 0.01077 0.00465 -0.0233 0.0027 1.0000
6.500 0.8219 0.01118 0.00507 -0.0226 0.0012 1.0000
6.750 0.8463 0.01155 0.00550 -0.0220 0.0010 1.0000
7.000 0.8704 0.01198 0.00600 -0.0214 0.0009 1.0000
7.250 0.8945 0.01243 0.00652 -0.0207 0.0008 1.0000
7.500 0.9181 0.01296 0.00714 -0.0201 0.0008 1.0000
7.750 0.9412 0.01356 0.00784 -0.0193 0.0007 1.0000
8.000 0.9640 0.01423 0.00862 -0.0185 0.0007 1.0000
8.250 0.9864 0.01494 0.00944 -0.0176 0.0007 1.0000
8.500 1.0080 0.01575 0.01042 -0.0167 0.0007 1.0000
8.750 1.0282 0.01678 0.01163 -0.0156 0.0007 1.0000
9.000 1.0478 0.01787 0.01289 -0.0144 0.0007 1.0000
9.250 1.0658 0.01917 0.01438 -0.0130 0.0007 1.0000
9.500 1.0835 0.02046 0.01586 -0.0117 0.0007 1.0000
9.750 1.0974 0.02230 0.01797 -0.0098 0.0007 1.0000
10.000 1.1111 0.02404 0.01995 -0.0081 0.0007 1.0000
10.250 1.1188 0.02650 0.02274 -0.0057 0.0007 1.0000
10.500 1.1240 0.02902 0.02556 -0.0033 0.0007 1.0000
10.750 1.1214 0.03216 0.02904 -0.0002 0.0007 1.0000
11.000 1.1126 0.03518 0.03236 0.0034 0.0007 1.0000
11.250 1.0928 0.03832 0.03574 0.0079 0.0007 1.0000
11.500 1.0850 0.04064 0.03821 0.0101 0.0007 1.0000
11.750 1.0584 0.04537 0.04317 0.0109 0.0007 1.0000
12.000 1.0439 0.04984 0.04779 0.0093 0.0007 1.0000
12.250 1.0157 0.05866 0.05681 0.0027 0.0007 1.0000
12.500 1.0099 0.06532 0.06356 -0.0028 0.0007 1.0000
12.750 0.9838 0.07820 0.07657 -0.0116 0.0007 1.0000
13.000 0.9466 0.09252 0.09097 -0.0192 0.0007 1.0000
13.250 0.9325 0.10052 0.09898 -0.0232 0.0007 1.0000
13.500 0.9037 0.11230 0.11078 -0.0291 0.0007 1.0000
13.750 0.8703 0.12599 0.12448 -0.0357 0.0008 1.0000
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