BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 200,000 Max Cl/Cd: 54.33 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr14-il-200000-n5.txt Download as CSV file: xf-vr14-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-14 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4464 0.08072 0.07753 -0.0070 1.0000 0.0115
-8.000 -0.5599 0.07861 0.07528 -0.0093 1.0000 0.0103
-7.750 -0.5564 0.07391 0.07056 -0.0128 1.0000 0.0101
-7.500 -0.5515 0.06902 0.06561 -0.0160 1.0000 0.0100
-7.250 -0.5449 0.06413 0.06063 -0.0186 1.0000 0.0099
-7.000 -0.5369 0.05904 0.05542 -0.0206 1.0000 0.0098
-6.750 -0.5273 0.05397 0.05018 -0.0219 1.0000 0.0097
-6.500 -0.5166 0.04885 0.04484 -0.0224 1.0000 0.0097
-6.250 -0.5053 0.04367 0.03938 -0.0221 1.0000 0.0097
-6.000 -0.4942 0.03866 0.03403 -0.0208 1.0000 0.0098
-5.750 -0.4862 0.03307 0.02795 -0.0179 1.0000 0.0101
-5.500 -0.4755 0.03051 0.02511 -0.0155 1.0000 0.0109
-5.250 -0.4465 0.02948 0.02392 -0.0167 0.9954 0.0121
-5.000 -0.4183 0.02521 0.01899 -0.0168 0.9895 0.0133
-4.750 -0.3886 0.02103 0.01400 -0.0166 0.9845 0.0143
-4.500 -0.3580 0.01957 0.01234 -0.0173 0.9792 0.0154
-4.250 -0.3263 0.01849 0.01108 -0.0181 0.9740 0.0173
-4.000 -0.2936 0.01746 0.00981 -0.0190 0.9697 0.0210
-3.750 -0.2639 0.01690 0.00918 -0.0195 0.9630 0.0241
-3.500 -0.2320 0.01628 0.00836 -0.0201 0.9579 0.0274
-3.250 -0.2048 0.01510 0.00718 -0.0200 0.9509 0.0301
-3.000 -0.1759 0.01461 0.00667 -0.0201 0.9444 0.0339
-2.750 -0.1496 0.01404 0.00603 -0.0196 0.9363 0.0363
-2.500 -0.1231 0.01349 0.00542 -0.0192 0.9295 0.0392
-2.250 -0.0984 0.01299 0.00492 -0.0185 0.9209 0.0430
-2.000 -0.0726 0.01264 0.00452 -0.0179 0.9141 0.0460
-1.750 -0.0478 0.01238 0.00419 -0.0169 0.9034 0.0504
-1.500 -0.0245 0.01201 0.00379 -0.0156 0.8901 0.0569
-1.250 -0.0014 0.01169 0.00345 -0.0141 0.8749 0.0698
-1.000 0.0197 0.01097 0.00316 -0.0126 0.8595 0.1926
-0.750 0.0298 0.00912 0.00295 -0.0092 0.8450 0.6318
-0.500 0.1385 0.00877 0.00337 -0.0243 0.8305 1.0000
-0.250 0.1628 0.00873 0.00319 -0.0233 0.8144 1.0000
0.000 0.1877 0.00871 0.00304 -0.0225 0.7981 1.0000
0.250 0.2126 0.00870 0.00291 -0.0217 0.7810 1.0000
0.500 0.2376 0.00871 0.00280 -0.0210 0.7621 1.0000
0.750 0.2627 0.00874 0.00270 -0.0202 0.7412 1.0000
1.000 0.2879 0.00878 0.00262 -0.0195 0.7149 1.0000
1.250 0.3131 0.00885 0.00255 -0.0188 0.6810 1.0000
1.500 0.3380 0.00899 0.00247 -0.0180 0.6319 1.0000
1.750 0.3622 0.00928 0.00239 -0.0171 0.5553 1.0000
2.000 0.3863 0.00978 0.00242 -0.0165 0.4645 1.0000
2.250 0.4108 0.01027 0.00254 -0.0161 0.3912 1.0000
2.500 0.4354 0.01070 0.00269 -0.0157 0.3404 1.0000
2.750 0.4603 0.01105 0.00287 -0.0153 0.3063 1.0000
3.000 0.4852 0.01137 0.00304 -0.0149 0.2821 1.0000
3.250 0.5102 0.01164 0.00322 -0.0145 0.2639 1.0000
3.500 0.5352 0.01191 0.00342 -0.0141 0.2492 1.0000
3.750 0.5601 0.01218 0.00366 -0.0136 0.2365 1.0000
4.000 0.5849 0.01247 0.00389 -0.0131 0.2253 1.0000
4.250 0.6097 0.01273 0.00413 -0.0126 0.2147 1.0000
4.500 0.6345 0.01301 0.00439 -0.0121 0.2049 1.0000
4.750 0.6589 0.01333 0.00468 -0.0116 0.1958 1.0000
5.000 0.6836 0.01360 0.00497 -0.0111 0.1866 1.0000
5.250 0.7080 0.01391 0.00527 -0.0106 0.1781 1.0000
5.500 0.7322 0.01424 0.00559 -0.0100 0.1692 1.0000
5.750 0.7567 0.01452 0.00592 -0.0095 0.1606 1.0000
6.000 0.7805 0.01489 0.00627 -0.0089 0.1543 1.0000
6.250 0.8049 0.01520 0.00666 -0.0084 0.1482 1.0000
6.500 0.8286 0.01557 0.00707 -0.0078 0.1423 1.0000
6.750 0.8526 0.01592 0.00750 -0.0072 0.1361 1.0000
7.000 0.8762 0.01630 0.00788 -0.0066 0.1283 1.0000
7.250 0.9002 0.01663 0.00829 -0.0060 0.1195 1.0000
7.500 0.9235 0.01703 0.00873 -0.0054 0.1114 1.0000
7.750 0.9469 0.01743 0.00920 -0.0048 0.1022 1.0000
8.000 0.9702 0.01786 0.00971 -0.0042 0.0929 1.0000
8.250 0.9929 0.01835 0.01025 -0.0036 0.0835 1.0000
8.500 1.0152 0.01891 0.01082 -0.0029 0.0730 1.0000
8.750 1.0367 0.01957 0.01148 -0.0022 0.0633 1.0000
9.000 1.0579 0.02027 0.01228 -0.0014 0.0563 1.0000
9.250 1.0778 0.02112 0.01318 -0.0005 0.0504 1.0000
9.500 1.0977 0.02195 0.01412 0.0004 0.0452 1.0000
9.750 1.1152 0.02304 0.01526 0.0015 0.0406 1.0000
10.000 1.1346 0.02388 0.01628 0.0025 0.0374 1.0000
10.250 1.1524 0.02485 0.01742 0.0036 0.0346 1.0000
10.500 1.1678 0.02603 0.01868 0.0049 0.0323 1.0000
10.750 1.1819 0.02729 0.02008 0.0063 0.0304 1.0000
11.000 1.1970 0.02840 0.02137 0.0076 0.0287 1.0000
11.250 1.2105 0.02958 0.02271 0.0090 0.0271 1.0000
11.500 1.2218 0.03088 0.02416 0.0105 0.0258 1.0000
11.750 1.2299 0.03235 0.02576 0.0123 0.0248 1.0000
12.000 1.2319 0.03405 0.02757 0.0147 0.0239 1.0000
12.250 1.2296 0.03621 0.02986 0.0171 0.0232 1.0000
12.500 1.2306 0.03825 0.03208 0.0188 0.0227 1.0000
12.750 1.2313 0.04042 0.03450 0.0200 0.0222 1.0000
13.000 1.2302 0.04291 0.03721 0.0209 0.0217 1.0000
13.250 1.2270 0.04578 0.04029 0.0212 0.0211 1.0000
13.500 1.2218 0.04911 0.04383 0.0208 0.0206 1.0000
13.750 1.2145 0.05299 0.04791 0.0198 0.0201 1.0000
14.000 1.2048 0.05756 0.05267 0.0179 0.0198 1.0000
14.250 1.1926 0.06297 0.05828 0.0151 0.0195 1.0000
14.500 1.1777 0.06938 0.06488 0.0113 0.0194 1.0000
14.750 1.1598 0.07680 0.07250 0.0067 0.0193 1.0000
15.000 1.1386 0.08523 0.08110 0.0015 0.0194 1.0000
15.250 1.1135 0.09454 0.09059 -0.0040 0.0195 1.0000
15.500 1.0842 0.10493 0.10113 -0.0099 0.0198 1.0000
15.750 1.0480 0.11708 0.11339 -0.0166 0.0202 1.0000
16.000 0.9975 0.13347 0.12990 -0.0255 0.0211 1.0000
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Polar data table (+)
Polar graphs
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