BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 500,000 Max Cl/Cd: 73.42 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr14-il-500000-n5.txt Download as CSV file: xf-vr14-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4490 0.10949 0.10738 0.0059 1.0000 0.0067
-10.000 -0.4489 0.10555 0.10346 0.0048 1.0000 0.0065
-9.750 -0.5755 0.11137 0.10916 0.0178 1.0000 0.0069
-9.500 -0.5724 0.10763 0.10544 0.0162 1.0000 0.0067
-9.250 -0.5703 0.10354 0.10136 0.0142 1.0000 0.0064
-9.000 -0.5691 0.09913 0.09696 0.0119 1.0000 0.0061
-8.750 -0.5691 0.09439 0.09225 0.0091 1.0000 0.0058
-8.500 -0.5734 0.08836 0.08625 0.0052 1.0000 0.0054
-8.000 -0.5855 0.07407 0.07196 -0.0079 1.0000 0.0048
-7.750 -0.5821 0.06820 0.06603 -0.0126 1.0000 0.0047
-7.500 -0.5766 0.06224 0.05998 -0.0164 1.0000 0.0047
-7.250 -0.5690 0.05627 0.05386 -0.0192 1.0000 0.0046
-7.000 -0.5605 0.04991 0.04730 -0.0209 1.0000 0.0045
-6.750 -0.5916 0.02056 0.01579 -0.0175 0.9787 0.0044
-6.500 -0.5684 0.01762 0.01231 -0.0169 0.9714 0.0047
-6.250 -0.5441 0.01618 0.01058 -0.0162 0.9641 0.0049
-6.000 -0.5202 0.01507 0.00926 -0.0154 0.9572 0.0052
-5.750 -0.4958 0.01441 0.00849 -0.0147 0.9497 0.0056
-5.500 -0.4718 0.01381 0.00777 -0.0138 0.9431 0.0060
-5.250 -0.4471 0.01318 0.00702 -0.0130 0.9358 0.0066
-5.000 -0.4233 0.01261 0.00633 -0.0120 0.9291 0.0071
-4.750 -0.3980 0.01214 0.00581 -0.0115 0.9218 0.0082
-4.500 -0.3730 0.01185 0.00546 -0.0107 0.9153 0.0097
-4.250 -0.3470 0.01153 0.00512 -0.0103 0.9082 0.0116
-4.000 -0.3214 0.01133 0.00489 -0.0096 0.9013 0.0135
-3.750 -0.2953 0.01105 0.00457 -0.0092 0.8936 0.0153
-3.500 -0.2692 0.01092 0.00440 -0.0086 0.8865 0.0173
-3.250 -0.2417 0.01091 0.00435 -0.0085 0.8790 0.0197
-3.000 -0.2163 0.01051 0.00394 -0.0079 0.8722 0.0222
-2.750 -0.1899 0.01026 0.00365 -0.0074 0.8626 0.0240
-2.500 -0.1639 0.01005 0.00337 -0.0069 0.8497 0.0261
-2.250 -0.1377 0.00988 0.00311 -0.0063 0.8345 0.0274
-2.000 -0.1120 0.00953 0.00269 -0.0057 0.8197 0.0295
-1.750 -0.0856 0.00934 0.00243 -0.0052 0.8040 0.0320
-1.500 -0.0589 0.00920 0.00221 -0.0048 0.7881 0.0344
-1.250 -0.0319 0.00908 0.00200 -0.0044 0.7723 0.0365
-1.000 -0.0047 0.00897 0.00182 -0.0042 0.7573 0.0407
-0.750 0.0226 0.00884 0.00166 -0.0039 0.7430 0.0492
-0.500 0.0493 0.00859 0.00153 -0.0037 0.7285 0.1003
-0.250 0.0739 0.00797 0.00141 -0.0033 0.7123 0.2747
0.000 0.0924 0.00673 0.00129 -0.0018 0.6939 0.6176
0.250 0.1438 0.00600 0.00153 -0.0062 0.6593 0.9616
0.500 0.1843 0.00633 0.00162 -0.0088 0.6063 0.9843
0.750 0.2432 0.00695 0.00172 -0.0158 0.4955 0.9981
1.000 0.2772 0.00737 0.00177 -0.0175 0.4140 1.0000
1.250 0.3046 0.00771 0.00180 -0.0177 0.3489 1.0000
1.500 0.3313 0.00796 0.00184 -0.0176 0.3085 1.0000
2.000 0.3839 0.00830 0.00194 -0.0172 0.2644 1.0000
2.250 0.4100 0.00844 0.00200 -0.0170 0.2491 1.0000
2.500 0.4361 0.00859 0.00207 -0.0167 0.2360 1.0000
2.750 0.4621 0.00874 0.00216 -0.0164 0.2242 1.0000
3.000 0.4880 0.00888 0.00225 -0.0161 0.2135 1.0000
3.250 0.5139 0.00903 0.00235 -0.0157 0.2033 1.0000
3.500 0.5396 0.00920 0.00246 -0.0154 0.1915 1.0000
3.750 0.5652 0.00938 0.00260 -0.0151 0.1799 1.0000
4.000 0.5908 0.00956 0.00273 -0.0147 0.1709 1.0000
4.250 0.6164 0.00972 0.00287 -0.0143 0.1643 1.0000
4.500 0.6419 0.00990 0.00304 -0.0139 0.1575 1.0000
4.750 0.6673 0.01008 0.00321 -0.0135 0.1511 1.0000
5.000 0.6926 0.01028 0.00339 -0.0131 0.1438 1.0000
5.250 0.7179 0.01048 0.00359 -0.0127 0.1383 1.0000
5.500 0.7431 0.01068 0.00380 -0.0122 0.1327 1.0000
5.750 0.7681 0.01093 0.00403 -0.0118 0.1272 1.0000
6.000 0.7933 0.01112 0.00425 -0.0114 0.1210 1.0000
6.500 0.8429 0.01162 0.00475 -0.0104 0.1079 1.0000
6.750 0.8674 0.01191 0.00503 -0.0100 0.1004 1.0000
7.000 0.8921 0.01216 0.00530 -0.0095 0.0940 1.0000
7.250 0.9163 0.01248 0.00561 -0.0090 0.0856 1.0000
7.500 0.9403 0.01283 0.00595 -0.0085 0.0749 1.0000
8.000 0.9872 0.01367 0.00674 -0.0073 0.0561 1.0000
8.250 1.0103 0.01411 0.00719 -0.0067 0.0496 1.0000
8.500 1.0331 0.01460 0.00768 -0.0060 0.0441 1.0000
8.750 1.0560 0.01505 0.00819 -0.0053 0.0399 1.0000
9.000 1.0789 0.01549 0.00869 -0.0047 0.0355 1.0000
9.250 1.1008 0.01607 0.00928 -0.0039 0.0308 1.0000
9.500 1.1230 0.01659 0.00984 -0.0032 0.0278 1.0000
9.750 1.1443 0.01721 0.01048 -0.0025 0.0249 1.0000
10.000 1.1653 0.01788 0.01121 -0.0016 0.0228 1.0000
10.250 1.1869 0.01841 0.01187 -0.0009 0.0215 1.0000
10.500 1.2079 0.01901 0.01254 -0.0001 0.0198 1.0000
10.750 1.2279 0.01972 0.01329 0.0007 0.0179 1.0000
11.000 1.2466 0.02055 0.01420 0.0017 0.0163 1.0000
11.250 1.2669 0.02114 0.01488 0.0025 0.0153 1.0000
11.500 1.2862 0.02182 0.01566 0.0034 0.0144 1.0000
11.750 1.3045 0.02257 0.01652 0.0044 0.0134 1.0000
12.000 1.3216 0.02341 0.01743 0.0054 0.0124 1.0000
12.250 1.3362 0.02445 0.01855 0.0067 0.0114 1.0000
12.500 1.3523 0.02526 0.01949 0.0079 0.0110 1.0000
12.750 1.3668 0.02616 0.02050 0.0092 0.0105 1.0000
13.000 1.3797 0.02710 0.02156 0.0106 0.0099 1.0000
13.250 1.3890 0.02811 0.02267 0.0125 0.0092 1.0000
13.500 1.3962 0.02928 0.02393 0.0144 0.0086 1.0000
13.750 1.4017 0.03067 0.02542 0.0161 0.0081 1.0000
14.000 1.4057 0.03227 0.02713 0.0176 0.0077 1.0000
14.250 1.4099 0.03394 0.02898 0.0187 0.0073 1.0000
14.500 1.4129 0.03586 0.03103 0.0196 0.0068 1.0000
14.750 1.4134 0.03816 0.03347 0.0200 0.0063 1.0000
15.000 1.4114 0.04094 0.03638 0.0200 0.0059 1.0000
15.250 1.4063 0.04432 0.03989 0.0194 0.0055 1.0000
15.500 1.3972 0.04858 0.04430 0.0180 0.0052 1.0000
15.750 1.3838 0.05398 0.04988 0.0153 0.0051 1.0000
16.000 1.3637 0.06133 0.05743 0.0109 0.0051 1.0000
16.250 1.3339 0.07138 0.06772 0.0046 0.0053 1.0000
16.500 1.2941 0.08342 0.07999 -0.0022 0.0058 1.0000
16.750 1.2483 0.09590 0.09266 -0.0085 0.0064 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-14 AIRFOIL (vr14-il)