BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 50,000 Max Cl/Cd: 29.06 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr13-il-50000-n5.txt Download as CSV file: xf-vr13-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5221 0.14003 0.13294 0.0086 1.0000 0.0943
-11.000 -0.5296 0.13780 0.13079 0.0045 1.0000 0.0972
-10.750 -0.5377 0.13532 0.12838 0.0002 1.0000 0.0979
-10.500 -0.5126 0.12894 0.12200 0.0038 1.0000 0.1017
-10.250 -0.5057 0.12527 0.11835 0.0031 1.0000 0.1050
-10.000 -0.5041 0.12183 0.11495 0.0011 1.0000 0.1088
-9.750 -0.5192 0.11945 0.11268 -0.0046 1.0000 0.1124
-9.250 -0.5012 0.11039 0.10367 -0.0047 1.0000 0.1160
-9.000 -0.4950 0.10656 0.09988 -0.0055 1.0000 0.1184
-8.750 -0.4099 0.08803 0.08168 -0.0250 1.0000 0.0687
-8.500 -0.4036 0.08387 0.07755 -0.0245 1.0000 0.0673
-8.250 -0.4054 0.07937 0.07309 -0.0258 1.0000 0.0658
-8.000 -0.5111 0.08218 0.07546 -0.0261 1.0000 0.0552
-7.750 -0.5081 0.07806 0.07133 -0.0268 1.0000 0.0546
-7.500 -0.5065 0.07389 0.06711 -0.0277 1.0000 0.0543
-7.250 -0.5046 0.06975 0.06287 -0.0283 1.0000 0.0541
-7.000 -0.5018 0.06574 0.05872 -0.0284 1.0000 0.0541
-6.750 -0.4978 0.06190 0.05469 -0.0279 1.0000 0.0539
-6.500 -0.4929 0.05825 0.05086 -0.0268 1.0000 0.0535
-6.250 -0.4877 0.05479 0.04719 -0.0253 1.0000 0.0530
-6.000 -0.4824 0.05153 0.04369 -0.0232 1.0000 0.0526
-5.750 -0.4762 0.04846 0.04032 -0.0209 1.0000 0.0525
-5.500 -0.4687 0.04562 0.03709 -0.0184 1.0000 0.0535
-5.250 -0.4596 0.04304 0.03399 -0.0157 1.0000 0.0551
-5.000 -0.4481 0.04069 0.03115 -0.0131 1.0000 0.0562
-4.750 -0.4347 0.03803 0.02822 -0.0111 1.0000 0.0569
-4.500 -0.4194 0.03588 0.02588 -0.0093 1.0000 0.0584
-4.250 -0.4029 0.03425 0.02406 -0.0077 1.0000 0.0616
-4.000 -0.3843 0.03256 0.02203 -0.0061 1.0000 0.0644
-3.750 -0.3635 0.03087 0.01995 -0.0046 1.0000 0.0660
-3.500 -0.3415 0.02947 0.01817 -0.0032 1.0000 0.0684
-3.250 -0.3196 0.02811 0.01672 -0.0023 1.0000 0.0723
-3.000 -0.2964 0.02702 0.01550 -0.0014 1.0000 0.0758
-2.750 -0.2718 0.02605 0.01437 -0.0005 1.0000 0.0791
-2.500 -0.2468 0.02528 0.01344 0.0001 1.0000 0.0848
-2.250 -0.2217 0.02455 0.01267 0.0004 1.0000 0.0910
-2.000 -0.1959 0.02398 0.01192 0.0008 0.9988 0.0968
-1.750 -0.1606 0.02333 0.01122 -0.0010 0.9934 0.1083
-1.500 -0.1259 0.02264 0.01066 -0.0027 0.9875 0.1355
-1.250 -0.0414 0.01949 0.01059 -0.0121 0.9967 1.0000
-1.000 -0.0040 0.01971 0.01042 -0.0145 0.9884 1.0000
-0.750 0.0355 0.01994 0.01034 -0.0174 0.9792 1.0000
-0.500 0.0763 0.02017 0.01032 -0.0204 0.9695 1.0000
-0.250 0.1212 0.02039 0.01033 -0.0241 0.9579 1.0000
0.000 0.1795 0.02043 0.01020 -0.0300 0.9403 1.0000
0.250 0.2389 0.02026 0.00990 -0.0355 0.9180 1.0000
0.500 0.2799 0.02012 0.00967 -0.0374 0.8962 1.0000
0.750 0.3142 0.02005 0.00954 -0.0381 0.8784 1.0000
1.000 0.3442 0.01997 0.00942 -0.0378 0.8598 1.0000
1.250 0.3692 0.01992 0.00934 -0.0366 0.8388 1.0000
1.500 0.3958 0.01977 0.00916 -0.0354 0.8175 1.0000
1.750 0.4189 0.01967 0.00905 -0.0336 0.7932 1.0000
2.000 0.4425 0.01953 0.00887 -0.0317 0.7671 1.0000
2.250 0.4646 0.01942 0.00873 -0.0297 0.7362 1.0000
2.500 0.4860 0.01934 0.00862 -0.0275 0.6986 1.0000
2.750 0.5071 0.01926 0.00845 -0.0251 0.6514 1.0000
3.000 0.5282 0.01926 0.00825 -0.0227 0.5881 1.0000
3.250 0.5485 0.01949 0.00803 -0.0202 0.5171 1.0000
3.500 0.5671 0.02006 0.00810 -0.0180 0.4562 1.0000
3.750 0.5865 0.02077 0.00845 -0.0163 0.4120 1.0000
4.000 0.6069 0.02150 0.00894 -0.0151 0.3799 1.0000
4.250 0.6280 0.02220 0.00945 -0.0140 0.3552 1.0000
4.500 0.6496 0.02292 0.00999 -0.0130 0.3363 1.0000
4.750 0.6721 0.02360 0.01059 -0.0121 0.3195 1.0000
5.000 0.6950 0.02430 0.01123 -0.0113 0.3052 1.0000
5.250 0.7186 0.02499 0.01191 -0.0106 0.2926 1.0000
5.500 0.7424 0.02569 0.01264 -0.0099 0.2810 1.0000
5.750 0.7662 0.02643 0.01341 -0.0093 0.2705 1.0000
6.000 0.7902 0.02720 0.01413 -0.0087 0.2615 1.0000
6.250 0.8142 0.02802 0.01511 -0.0081 0.2529 1.0000
6.500 0.8386 0.02887 0.01590 -0.0075 0.2460 1.0000
6.750 0.8615 0.02978 0.01707 -0.0069 0.2376 1.0000
7.000 0.8851 0.03067 0.01792 -0.0063 0.2308 1.0000
7.250 0.9070 0.03174 0.01928 -0.0056 0.2235 1.0000
7.500 0.9302 0.03277 0.02037 -0.0050 0.2178 1.0000
7.750 0.9512 0.03398 0.02186 -0.0042 0.2113 1.0000
8.000 0.9722 0.03505 0.02308 -0.0034 0.2045 1.0000
8.250 0.9922 0.03627 0.02448 -0.0025 0.1981 1.0000
8.500 1.0107 0.03745 0.02589 -0.0015 0.1907 1.0000
8.750 1.0290 0.03857 0.02718 -0.0005 0.1836 1.0000
9.000 1.0454 0.03982 0.02868 0.0006 0.1762 1.0000
9.250 1.0634 0.04105 0.03004 0.0016 0.1702 1.0000
9.500 1.0756 0.04294 0.03233 0.0030 0.1638 1.0000
9.750 1.0956 0.04384 0.03322 0.0039 0.1583 1.0000
10.000 1.1002 0.04625 0.03616 0.0058 0.1514 1.0000
10.250 1.1157 0.04733 0.03732 0.0070 0.1455 1.0000
10.500 1.1202 0.04987 0.04021 0.0087 0.1406 1.0000
10.750 1.1199 0.05256 0.04326 0.0107 0.1354 1.0000
11.000 1.1414 0.05290 0.04350 0.0115 0.1301 1.0000
11.250 1.1202 0.05719 0.04831 0.0143 0.1263 1.0000
11.500 1.1018 0.06079 0.05219 0.0166 0.1229 1.0000
11.750 1.1009 0.06266 0.05415 0.0183 0.1190 1.0000
12.000 1.1007 0.06476 0.05630 0.0195 0.1157 1.0000
12.250 1.0599 0.07150 0.06328 0.0191 0.1153 1.0000
12.500 1.0087 0.08138 0.07332 0.0149 0.1156 1.0000
12.750 0.9310 0.09978 0.09169 0.0035 0.1161 1.0000
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Polar data table (+)
Polar graphs
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