RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 100,000 Max Cl/Cd: 45.73 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14a147-il-100000-n5.txt Download as CSV file: xf-rg14a147-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14A-1.4/7.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4368 0.08942 0.08471 -0.0149 1.0000 0.0234
-8.750 -0.4370 0.08516 0.08048 -0.0159 1.0000 0.0226
-8.500 -0.5186 0.09006 0.08515 -0.0149 1.0000 0.0235
-8.250 -0.5186 0.08620 0.08134 -0.0163 1.0000 0.0226
-8.000 -0.5207 0.08222 0.07743 -0.0183 1.0000 0.0219
-7.750 -0.5253 0.07798 0.07325 -0.0209 1.0000 0.0212
-7.500 -0.5262 0.07315 0.06844 -0.0243 1.0000 0.0204
-7.250 -0.5252 0.06823 0.06349 -0.0273 1.0000 0.0197
-7.000 -0.5230 0.06292 0.05811 -0.0298 1.0000 0.0189
-6.750 -0.5191 0.05713 0.05217 -0.0318 1.0000 0.0178
-6.500 -0.5125 0.05060 0.04530 -0.0329 1.0000 0.0166
-6.250 -0.4998 0.04651 0.04088 -0.0326 1.0000 0.0159
-5.750 -0.4741 0.03938 0.03307 -0.0310 1.0000 0.0155
-5.500 -0.4597 0.03576 0.02895 -0.0301 1.0000 0.0154
-5.000 -0.4270 0.02908 0.02143 -0.0281 1.0000 0.0172
-4.750 -0.4072 0.02741 0.01954 -0.0272 1.0000 0.0196
-4.500 -0.3854 0.02513 0.01684 -0.0260 1.0000 0.0207
-4.250 -0.3626 0.02290 0.01420 -0.0247 1.0000 0.0213
-4.000 -0.3393 0.02100 0.01199 -0.0233 1.0000 0.0224
-3.750 -0.3162 0.01941 0.01018 -0.0220 1.0000 0.0239
-3.500 -0.2942 0.01798 0.00863 -0.0208 1.0000 0.0265
-3.250 -0.2722 0.01710 0.00772 -0.0198 1.0000 0.0347
-3.000 -0.2500 0.01602 0.00652 -0.0186 1.0000 0.0407
-2.750 -0.2275 0.01509 0.00558 -0.0175 1.0000 0.0601
-2.500 -0.2059 0.01397 0.00490 -0.0167 1.0000 0.1530
-2.250 -0.1868 0.01244 0.00463 -0.0159 1.0000 0.4229
-2.000 -0.1734 0.01139 0.00470 -0.0122 1.0000 0.6991
-1.750 -0.1528 0.01121 0.00483 -0.0090 1.0000 0.8904
-1.500 -0.0780 0.01116 0.00449 -0.0179 1.0000 1.0000
-1.250 -0.0636 0.01117 0.00434 -0.0159 1.0000 1.0000
-1.000 -0.0446 0.01122 0.00418 -0.0147 0.9991 1.0000
-0.750 -0.0024 0.01132 0.00410 -0.0181 0.9896 1.0000
-0.500 0.0394 0.01142 0.00405 -0.0213 0.9799 1.0000
-0.250 0.0805 0.01147 0.00400 -0.0243 0.9693 1.0000
0.000 0.1197 0.01148 0.00390 -0.0268 0.9572 1.0000
0.250 0.1591 0.01147 0.00384 -0.0293 0.9448 1.0000
0.500 0.1981 0.01144 0.00378 -0.0316 0.9316 1.0000
0.750 0.2360 0.01140 0.00374 -0.0336 0.9169 1.0000
1.000 0.2723 0.01137 0.00370 -0.0351 0.8998 1.0000
1.250 0.3067 0.01133 0.00367 -0.0363 0.8798 1.0000
1.500 0.3411 0.01131 0.00365 -0.0373 0.8584 1.0000
1.750 0.3738 0.01130 0.00367 -0.0379 0.8345 1.0000
2.000 0.4033 0.01133 0.00369 -0.0378 0.8068 1.0000
2.250 0.4313 0.01140 0.00374 -0.0374 0.7761 1.0000
2.500 0.4589 0.01151 0.00380 -0.0368 0.7449 1.0000
2.750 0.4844 0.01167 0.00400 -0.0360 0.7110 1.0000
3.000 0.5087 0.01186 0.00415 -0.0349 0.6720 1.0000
3.250 0.5327 0.01210 0.00431 -0.0338 0.6310 1.0000
3.500 0.5560 0.01239 0.00451 -0.0325 0.5863 1.0000
3.750 0.5788 0.01275 0.00474 -0.0313 0.5389 1.0000
4.000 0.6013 0.01315 0.00503 -0.0300 0.4881 1.0000
4.250 0.6232 0.01363 0.00545 -0.0288 0.4336 1.0000
4.500 0.6447 0.01419 0.00584 -0.0276 0.3746 1.0000
4.750 0.6656 0.01486 0.00630 -0.0264 0.3086 1.0000
5.000 0.6855 0.01573 0.00684 -0.0253 0.2301 1.0000
5.250 0.7045 0.01687 0.00749 -0.0242 0.1429 1.0000
5.500 0.7248 0.01798 0.00837 -0.0232 0.0904 1.0000
5.750 0.7442 0.01931 0.00947 -0.0221 0.0575 1.0000
6.000 0.7646 0.02047 0.01067 -0.0209 0.0428 1.0000
6.250 0.7848 0.02168 0.01202 -0.0197 0.0365 1.0000
6.500 0.8032 0.02325 0.01384 -0.0182 0.0332 1.0000
6.750 0.8235 0.02484 0.01566 -0.0168 0.0309 1.0000
7.000 0.8445 0.02673 0.01778 -0.0155 0.0286 1.0000
7.250 0.8639 0.02828 0.01943 -0.0146 0.0242 1.0000
7.500 0.8830 0.03103 0.02249 -0.0134 0.0218 1.0000
7.750 0.9019 0.03391 0.02583 -0.0119 0.0204 1.0000
8.000 0.9177 0.03683 0.02924 -0.0103 0.0185 1.0000
8.250 0.9317 0.03877 0.03148 -0.0091 0.0159 1.0000
8.500 0.9413 0.04146 0.03441 -0.0079 0.0145 1.0000
9.000 0.9410 0.05013 0.04395 -0.0042 0.0137 1.0000
9.250 0.9360 0.05403 0.04826 -0.0024 0.0136 1.0000
9.500 0.9263 0.05785 0.05239 -0.0008 0.0135 1.0000
9.750 0.9108 0.06152 0.05629 0.0008 0.0135 1.0000
10.000 0.8939 0.06565 0.06060 0.0006 0.0135 1.0000
10.250 0.8771 0.07059 0.06568 -0.0016 0.0137 1.0000
10.500 0.8600 0.07675 0.07196 -0.0059 0.0137 1.0000
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Polar data table (+)
Polar graphs
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