BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.63 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr15-il-1000000.txt Download as CSV file: xf-vr15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-15 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6227 0.10103 0.09950 0.0161 1.0000 0.0102
-9.250 -0.6232 0.09610 0.09459 0.0134 1.0000 0.0102
-9.000 -0.8831 0.02307 0.01940 -0.0072 1.0000 0.0053
-8.750 -0.8671 0.02032 0.01625 -0.0058 1.0000 0.0053
-8.500 -0.8474 0.01837 0.01401 -0.0047 1.0000 0.0054
-8.250 -0.8254 0.01693 0.01234 -0.0040 1.0000 0.0055
-8.000 -0.8018 0.01583 0.01106 -0.0034 1.0000 0.0057
-7.750 -0.7774 0.01493 0.01003 -0.0029 1.0000 0.0059
-7.500 -0.7524 0.01416 0.00914 -0.0024 1.0000 0.0061
-7.250 -0.7273 0.01346 0.00835 -0.0020 1.0000 0.0065
-7.000 -0.7025 0.01284 0.00763 -0.0015 1.0000 0.0070
-6.750 -0.6801 0.01207 0.00676 -0.0005 1.0000 0.0079
-6.500 -0.6488 0.01172 0.00639 -0.0013 0.9969 0.0095
-6.250 -0.6156 0.01140 0.00607 -0.0026 0.9941 0.0117
-6.000 -0.5834 0.01144 0.00614 -0.0036 0.9889 0.0132
-5.750 -0.5521 0.01118 0.00584 -0.0044 0.9841 0.0144
-5.500 -0.5236 0.01117 0.00587 -0.0045 0.9774 0.0155
-5.000 -0.4724 0.01109 0.00576 -0.0033 0.9625 0.0177
-4.750 -0.4482 0.01112 0.00575 -0.0023 0.9554 0.0184
-4.500 -0.4260 0.01045 0.00501 -0.0011 0.9474 0.0198
-4.250 -0.4015 0.01033 0.00491 -0.0002 0.9401 0.0212
-4.000 -0.3755 0.01038 0.00496 0.0003 0.9324 0.0228
-3.750 -0.3498 0.01026 0.00482 0.0009 0.9255 0.0242
-3.500 -0.3233 0.01024 0.00477 0.0013 0.9179 0.0251
-3.250 -0.3007 0.00931 0.00374 0.0026 0.9093 0.0269
-3.000 -0.2761 0.00901 0.00341 0.0034 0.8989 0.0286
-2.750 -0.2504 0.00880 0.00317 0.0041 0.8868 0.0301
-2.500 -0.2241 0.00857 0.00289 0.0046 0.8751 0.0314
-2.250 -0.1977 0.00837 0.00263 0.0050 0.8630 0.0325
-2.000 -0.1710 0.00821 0.00241 0.0055 0.8502 0.0333
-1.750 -0.1440 0.00809 0.00225 0.0058 0.8373 0.0339
-1.500 -0.1174 0.00782 0.00188 0.0062 0.8247 0.0352
-1.000 -0.0629 0.00747 0.00146 0.0068 0.8012 0.0431
-0.750 -0.0357 0.00729 0.00130 0.0070 0.7894 0.0633
-0.500 -0.0127 0.00644 0.00115 0.0077 0.7776 0.2876
-0.250 0.0076 0.00544 0.00102 0.0089 0.7657 0.5648
0.000 0.0238 0.00451 0.00094 0.0115 0.7524 0.8161
0.250 0.0612 0.00429 0.00108 0.0099 0.7342 0.9469
0.500 0.1048 0.00454 0.00123 0.0067 0.7097 0.9731
0.750 0.1614 0.00494 0.00151 0.0005 0.6770 0.9887
1.000 0.2172 0.00531 0.00165 -0.0056 0.6234 0.9970
1.250 0.2586 0.00567 0.00167 -0.0088 0.5372 0.9995
1.500 0.2913 0.00608 0.00171 -0.0102 0.4431 1.0000
1.750 0.3203 0.00646 0.00175 -0.0107 0.3591 1.0000
2.000 0.3483 0.00675 0.00179 -0.0110 0.3036 1.0000
2.250 0.3757 0.00693 0.00183 -0.0111 0.2712 1.0000
2.500 0.4027 0.00707 0.00188 -0.0110 0.2504 1.0000
2.750 0.4297 0.00720 0.00193 -0.0110 0.2336 1.0000
3.000 0.4565 0.00731 0.00198 -0.0109 0.2194 1.0000
3.250 0.4832 0.00743 0.00204 -0.0107 0.2067 1.0000
3.500 0.5098 0.00755 0.00213 -0.0105 0.1954 1.0000
3.750 0.5362 0.00768 0.00221 -0.0103 0.1847 1.0000
4.000 0.5623 0.00783 0.00231 -0.0100 0.1734 1.0000
4.250 0.5882 0.00796 0.00241 -0.0097 0.1644 1.0000
4.500 0.6141 0.00810 0.00253 -0.0094 0.1563 1.0000
4.750 0.6398 0.00828 0.00266 -0.0091 0.1463 1.0000
5.000 0.6656 0.00842 0.00278 -0.0087 0.1379 1.0000
5.250 0.6912 0.00860 0.00294 -0.0084 0.1302 1.0000
5.500 0.7167 0.00876 0.00309 -0.0080 0.1231 1.0000
5.750 0.7422 0.00894 0.00326 -0.0076 0.1163 1.0000
6.000 0.7675 0.00913 0.00342 -0.0072 0.1087 1.0000
6.250 0.7928 0.00933 0.00362 -0.0068 0.1014 1.0000
6.500 0.8177 0.00958 0.00383 -0.0063 0.0917 1.0000
6.750 0.8426 0.00984 0.00405 -0.0059 0.0808 1.0000
7.000 0.8669 0.01019 0.00433 -0.0054 0.0655 1.0000
7.250 0.8909 0.01058 0.00466 -0.0049 0.0546 1.0000
7.500 0.9149 0.01095 0.00502 -0.0043 0.0477 1.0000
7.750 0.9390 0.01128 0.00536 -0.0037 0.0414 1.0000
8.000 0.9623 0.01176 0.00580 -0.0031 0.0334 1.0000
8.250 0.9858 0.01216 0.00619 -0.0024 0.0293 1.0000
8.500 1.0086 0.01270 0.00675 -0.0016 0.0253 1.0000
8.750 1.0321 0.01305 0.00715 -0.0010 0.0238 1.0000
9.000 1.0550 0.01350 0.00764 -0.0003 0.0220 1.0000
9.250 1.0763 0.01419 0.00837 0.0007 0.0196 1.0000
9.500 1.0981 0.01475 0.00900 0.0016 0.0185 1.0000
9.750 1.1208 0.01516 0.00948 0.0023 0.0177 1.0000
10.000 1.1428 0.01565 0.01003 0.0031 0.0169 1.0000
10.250 1.1643 0.01617 0.01061 0.0040 0.0160 1.0000
10.500 1.1847 0.01682 0.01131 0.0049 0.0151 1.0000
10.750 1.2012 0.01793 0.01252 0.0065 0.0141 1.0000
11.000 1.2174 0.01898 0.01371 0.0080 0.0135 1.0000
11.250 1.2383 0.01944 0.01425 0.0089 0.0132 1.0000
11.500 1.2588 0.01991 0.01478 0.0097 0.0126 1.0000
11.750 1.2786 0.02043 0.01536 0.0107 0.0120 1.0000
12.000 1.2976 0.02102 0.01599 0.0117 0.0115 1.0000
12.250 1.3151 0.02172 0.01675 0.0129 0.0110 1.0000
12.500 1.3297 0.02267 0.01777 0.0144 0.0106 1.0000
12.750 1.3373 0.02418 0.01941 0.0167 0.0101 1.0000
13.000 1.3381 0.02614 0.02158 0.0196 0.0097 1.0000
13.250 1.3507 0.02692 0.02245 0.0212 0.0096 1.0000
13.500 1.3578 0.02790 0.02353 0.0235 0.0094 1.0000
13.750 1.3644 0.02904 0.02477 0.0254 0.0092 1.0000
14.000 1.3688 0.03047 0.02631 0.0271 0.0091 1.0000
14.250 1.3727 0.03208 0.02804 0.0284 0.0089 1.0000
14.500 1.3740 0.03408 0.03016 0.0294 0.0087 1.0000
14.750 1.3744 0.03636 0.03257 0.0299 0.0085 1.0000
15.000 1.3729 0.03908 0.03541 0.0298 0.0084 1.0000
15.250 1.3695 0.04232 0.03877 0.0290 0.0082 1.0000
15.500 1.3633 0.04626 0.04284 0.0275 0.0081 1.0000
15.750 1.3528 0.05136 0.04809 0.0247 0.0080 1.0000
16.000 1.3340 0.05862 0.05552 0.0201 0.0080 1.0000
16.250 1.3056 0.06847 0.06558 0.0137 0.0081 1.0000
16.500 1.2692 0.07969 0.07699 0.0073 0.0082 1.0000
16.750 1.2277 0.09115 0.08860 0.0013 0.0083 1.0000
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Polar data table (+)
Polar graphs
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