RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 100,000 Max Cl/Cd: 46.55 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1495-il-100000-n5.txt Download as CSV file: xf-rg1495-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5317 0.09029 0.08509 -0.0276 1.0000 0.0295
-9.750 -0.5390 0.08465 0.07952 -0.0305 1.0000 0.0292
-9.500 -0.5504 0.07805 0.07299 -0.0345 1.0000 0.0291
-9.250 -0.5675 0.06985 0.06485 -0.0410 1.0000 0.0284
-9.000 -0.5933 0.06335 0.05831 -0.0437 1.0000 0.0279
-8.750 -0.6147 0.05792 0.05278 -0.0439 1.0000 0.0277
-8.500 -0.6298 0.05299 0.04763 -0.0431 1.0000 0.0277
-8.250 -0.6382 0.04869 0.04304 -0.0416 1.0000 0.0281
-8.000 -0.6415 0.04471 0.03869 -0.0398 1.0000 0.0291
-7.750 -0.6411 0.04087 0.03438 -0.0377 1.0000 0.0303
-7.500 -0.6364 0.03732 0.03025 -0.0355 1.0000 0.0312
-7.250 -0.6270 0.03430 0.02670 -0.0334 1.0000 0.0317
-7.000 -0.6147 0.03154 0.02356 -0.0315 1.0000 0.0325
-6.750 -0.5993 0.02971 0.02160 -0.0301 1.0000 0.0338
-6.500 -0.5822 0.02849 0.02023 -0.0287 1.0000 0.0359
-6.250 -0.5642 0.02702 0.01849 -0.0272 1.0000 0.0381
-6.000 -0.5451 0.02537 0.01654 -0.0256 1.0000 0.0395
-5.750 -0.5252 0.02393 0.01481 -0.0242 1.0000 0.0410
-5.500 -0.5055 0.02261 0.01335 -0.0228 1.0000 0.0426
-5.250 -0.4864 0.02169 0.01245 -0.0215 1.0000 0.0459
-5.000 -0.4664 0.02086 0.01153 -0.0202 1.0000 0.0493
-4.750 -0.4463 0.01999 0.01053 -0.0188 1.0000 0.0523
-4.500 -0.4270 0.01910 0.00962 -0.0174 1.0000 0.0558
-4.250 -0.4072 0.01843 0.00890 -0.0161 1.0000 0.0613
-4.000 -0.3872 0.01782 0.00829 -0.0149 1.0000 0.0705
-3.750 -0.3625 0.01722 0.00773 -0.0147 0.9984 0.0863
-3.500 -0.3270 0.01659 0.00722 -0.0167 0.9926 0.1159
-3.250 -0.2924 0.01597 0.00684 -0.0186 0.9862 0.1695
-3.000 -0.2589 0.01531 0.00657 -0.0203 0.9797 0.2509
-2.750 -0.2258 0.01465 0.00634 -0.0219 0.9726 0.3528
-2.500 -0.1953 0.01398 0.00618 -0.0227 0.9649 0.4759
-2.250 -0.1649 0.01335 0.00620 -0.0228 0.9580 0.6348
-2.000 -0.1378 0.01319 0.00644 -0.0213 0.9494 0.7705
-1.750 -0.1021 0.01322 0.00648 -0.0218 0.9429 0.8428
-1.500 -0.0682 0.01326 0.00646 -0.0222 0.9340 0.8865
-1.250 -0.0205 0.01331 0.00641 -0.0254 0.9294 0.9199
-1.000 0.0285 0.01334 0.00633 -0.0292 0.9228 0.9454
-0.750 0.0841 0.01332 0.00621 -0.0344 0.9173 0.9634
-0.500 0.1417 0.01324 0.00602 -0.0403 0.9112 0.9771
-0.250 0.1961 0.01309 0.00580 -0.0456 0.9021 0.9889
0.000 0.2478 0.01292 0.00557 -0.0505 0.8907 0.9989
0.250 0.2831 0.01277 0.00537 -0.0520 0.8749 1.0000
0.500 0.3150 0.01264 0.00519 -0.0527 0.8579 1.0000
0.750 0.3449 0.01254 0.00504 -0.0530 0.8397 1.0000
1.000 0.3710 0.01248 0.00495 -0.0525 0.8194 1.0000
1.250 0.3975 0.01244 0.00485 -0.0520 0.7993 1.0000
1.500 0.4221 0.01244 0.00482 -0.0512 0.7781 1.0000
1.750 0.4461 0.01246 0.00478 -0.0502 0.7559 1.0000
2.000 0.4689 0.01251 0.00477 -0.0490 0.7309 1.0000
2.250 0.4912 0.01258 0.00476 -0.0476 0.7045 1.0000
2.500 0.5128 0.01269 0.00480 -0.0461 0.6767 1.0000
2.750 0.5339 0.01284 0.00484 -0.0445 0.6476 1.0000
3.000 0.5548 0.01301 0.00492 -0.0429 0.6192 1.0000
3.500 0.5967 0.01343 0.00523 -0.0399 0.5665 1.0000
3.750 0.6177 0.01367 0.00541 -0.0384 0.5400 1.0000
4.000 0.6383 0.01395 0.00561 -0.0369 0.5105 1.0000
4.250 0.6585 0.01427 0.00582 -0.0353 0.4780 1.0000
4.500 0.6786 0.01462 0.00609 -0.0338 0.4431 1.0000
4.750 0.6987 0.01501 0.00637 -0.0323 0.4068 1.0000
5.000 0.7186 0.01545 0.00669 -0.0308 0.3691 1.0000
5.250 0.7382 0.01595 0.00705 -0.0294 0.3303 1.0000
5.500 0.7579 0.01650 0.00749 -0.0280 0.2908 1.0000
5.750 0.7773 0.01711 0.00797 -0.0267 0.2528 1.0000
6.000 0.7967 0.01779 0.00850 -0.0254 0.2186 1.0000
6.250 0.8161 0.01849 0.00910 -0.0241 0.1901 1.0000
6.500 0.8355 0.01923 0.00975 -0.0229 0.1679 1.0000
6.750 0.8547 0.02000 0.01051 -0.0217 0.1496 1.0000
7.000 0.8739 0.02080 0.01129 -0.0204 0.1341 1.0000
7.250 0.8932 0.02158 0.01210 -0.0192 0.1201 1.0000
7.500 0.9126 0.02236 0.01292 -0.0181 0.1078 1.0000
7.750 0.9314 0.02320 0.01380 -0.0168 0.0977 1.0000
8.000 0.9493 0.02411 0.01472 -0.0155 0.0889 1.0000
8.250 0.9678 0.02502 0.01575 -0.0142 0.0811 1.0000
8.500 0.9846 0.02611 0.01688 -0.0128 0.0750 1.0000
8.750 1.0022 0.02710 0.01798 -0.0115 0.0682 1.0000
9.000 1.0178 0.02837 0.01929 -0.0101 0.0635 1.0000
9.250 1.0351 0.02960 0.02071 -0.0087 0.0587 1.0000
9.500 1.0494 0.03080 0.02198 -0.0073 0.0542 1.0000
9.750 1.0646 0.03221 0.02360 -0.0058 0.0498 1.0000
10.000 1.0780 0.03345 0.02500 -0.0043 0.0455 1.0000
10.250 1.0877 0.03491 0.02645 -0.0026 0.0421 1.0000
10.500 1.0983 0.03642 0.02831 -0.0006 0.0384 1.0000
10.750 1.1053 0.03782 0.02987 0.0015 0.0355 1.0000
11.000 1.1094 0.03937 0.03148 0.0036 0.0334 1.0000
11.250 1.1129 0.04168 0.03397 0.0056 0.0317 1.0000
11.500 1.1142 0.04410 0.03673 0.0076 0.0300 1.0000
11.750 1.1129 0.04649 0.03941 0.0093 0.0284 1.0000
12.000 1.1107 0.04867 0.04174 0.0105 0.0268 1.0000
12.250 1.1076 0.05118 0.04437 0.0113 0.0258 1.0000
12.500 1.1032 0.05397 0.04725 0.0116 0.0250 1.0000
12.750 1.0933 0.05788 0.05137 0.0114 0.0244 1.0000
13.000 1.0804 0.06248 0.05626 0.0104 0.0240 1.0000
13.250 1.0649 0.06777 0.06182 0.0085 0.0238 1.0000
13.500 1.0475 0.07378 0.06807 0.0055 0.0237 1.0000
13.750 1.0276 0.08074 0.07524 0.0016 0.0237 1.0000
14.000 1.0053 0.08878 0.08348 -0.0035 0.0238 1.0000
14.250 0.9811 0.09794 0.09281 -0.0095 0.0240 1.0000
14.500 0.9561 0.10804 0.10303 -0.0159 0.0244 1.0000
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Polar data table (+)
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