RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 100,000 Max Cl/Cd: 46.62 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg149-il-100000-n5.txt Download as CSV file: xf-rg149-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9% 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5307 0.08951 0.08439 -0.0268 1.0000 0.0284
-9.500 -0.5362 0.08412 0.07907 -0.0296 1.0000 0.0284
-9.250 -0.5438 0.07833 0.07333 -0.0331 1.0000 0.0282
-9.000 -0.5555 0.07171 0.06677 -0.0382 1.0000 0.0280
-8.750 -0.5708 0.06657 0.06163 -0.0404 1.0000 0.0276
-8.500 -0.5859 0.06133 0.05630 -0.0414 1.0000 0.0274
-8.250 -0.5969 0.05650 0.05132 -0.0414 1.0000 0.0272
-8.000 -0.6058 0.05160 0.04618 -0.0407 1.0000 0.0272
-7.750 -0.6101 0.04704 0.04129 -0.0394 1.0000 0.0273
-7.500 -0.6104 0.04261 0.03643 -0.0377 1.0000 0.0275
-7.250 -0.6061 0.03861 0.03194 -0.0358 1.0000 0.0279
-7.000 -0.5973 0.03517 0.02793 -0.0338 1.0000 0.0286
-6.750 -0.5855 0.03247 0.02489 -0.0322 1.0000 0.0302
-6.500 -0.5695 0.03099 0.02324 -0.0309 1.0000 0.0321
-6.250 -0.5527 0.02896 0.02089 -0.0294 1.0000 0.0335
-6.000 -0.5345 0.02696 0.01854 -0.0278 1.0000 0.0347
-5.750 -0.5150 0.02526 0.01652 -0.0264 1.0000 0.0365
-5.500 -0.4944 0.02414 0.01504 -0.0250 1.0000 0.0391
-5.250 -0.4748 0.02252 0.01338 -0.0238 1.0000 0.0413
-5.000 -0.4544 0.02140 0.01218 -0.0225 1.0000 0.0431
-4.750 -0.4338 0.02041 0.01106 -0.0212 1.0000 0.0455
-4.500 -0.4132 0.01953 0.01008 -0.0199 1.0000 0.0485
-4.250 -0.3930 0.01875 0.00924 -0.0186 1.0000 0.0530
-4.000 -0.3726 0.01810 0.00858 -0.0175 1.0000 0.0591
-3.750 -0.3521 0.01740 0.00783 -0.0162 1.0000 0.0658
-3.500 -0.3313 0.01679 0.00723 -0.0151 1.0000 0.0782
-3.250 -0.3038 0.01618 0.00672 -0.0155 0.9974 0.1065
-3.000 -0.2687 0.01550 0.00637 -0.0176 0.9912 0.1686
-2.750 -0.2348 0.01470 0.00615 -0.0195 0.9849 0.2848
-2.500 -0.2031 0.01395 0.00596 -0.0208 0.9775 0.4189
-2.250 -0.1718 0.01320 0.00590 -0.0214 0.9709 0.5913
-2.000 -0.1463 0.01288 0.00617 -0.0196 0.9624 0.7633
-1.750 -0.1120 0.01292 0.00625 -0.0198 0.9555 0.8506
-1.500 -0.0750 0.01296 0.00622 -0.0208 0.9475 0.9014
-1.250 -0.0233 0.01303 0.00617 -0.0249 0.9437 0.9383
-1.000 0.0324 0.01305 0.00605 -0.0302 0.9390 0.9646
-0.750 0.0902 0.01300 0.00588 -0.0362 0.9342 0.9828
-0.500 0.1513 0.01287 0.00564 -0.0430 0.9298 0.9970
-0.250 0.1908 0.01274 0.00544 -0.0455 0.9174 1.0000
0.000 0.2259 0.01261 0.00525 -0.0470 0.9031 1.0000
0.250 0.2604 0.01248 0.00508 -0.0483 0.8879 1.0000
0.500 0.2941 0.01236 0.00491 -0.0494 0.8718 1.0000
0.750 0.3242 0.01228 0.00478 -0.0497 0.8533 1.0000
1.000 0.3530 0.01222 0.00469 -0.0497 0.8339 1.0000
1.250 0.3817 0.01218 0.00460 -0.0496 0.8144 1.0000
1.500 0.4070 0.01218 0.00457 -0.0489 0.7926 1.0000
1.750 0.4330 0.01220 0.00454 -0.0482 0.7707 1.0000
2.000 0.4566 0.01225 0.00454 -0.0471 0.7454 1.0000
2.250 0.4799 0.01233 0.00455 -0.0459 0.7181 1.0000
2.500 0.5025 0.01244 0.00459 -0.0445 0.6884 1.0000
2.750 0.5245 0.01259 0.00464 -0.0431 0.6581 1.0000
3.000 0.5463 0.01277 0.00473 -0.0416 0.6282 1.0000
3.250 0.5681 0.01298 0.00487 -0.0402 0.6003 1.0000
3.500 0.5900 0.01321 0.00506 -0.0389 0.5725 1.0000
3.750 0.6117 0.01347 0.00525 -0.0375 0.5432 1.0000
4.000 0.6330 0.01377 0.00545 -0.0361 0.5104 1.0000
4.250 0.6539 0.01410 0.00568 -0.0347 0.4735 1.0000
4.500 0.6746 0.01448 0.00594 -0.0332 0.4347 1.0000
4.750 0.6951 0.01491 0.00626 -0.0318 0.3948 1.0000
5.000 0.7153 0.01540 0.00661 -0.0304 0.3518 1.0000
5.250 0.7354 0.01595 0.00701 -0.0291 0.3080 1.0000
5.500 0.7553 0.01657 0.00747 -0.0278 0.2646 1.0000
5.750 0.7750 0.01726 0.00803 -0.0266 0.2253 1.0000
6.000 0.7949 0.01799 0.00863 -0.0254 0.1914 1.0000
6.250 0.8146 0.01876 0.00929 -0.0243 0.1662 1.0000
6.500 0.8343 0.01955 0.01003 -0.0231 0.1456 1.0000
6.750 0.8539 0.02037 0.01082 -0.0219 0.1285 1.0000
7.000 0.8736 0.02117 0.01163 -0.0208 0.1138 1.0000
7.250 0.8935 0.02197 0.01249 -0.0197 0.1008 1.0000
7.500 0.9131 0.02281 0.01340 -0.0185 0.0904 1.0000
7.750 0.9320 0.02374 0.01439 -0.0173 0.0811 1.0000
8.000 0.9493 0.02481 0.01543 -0.0160 0.0738 1.0000
8.250 0.9683 0.02587 0.01668 -0.0147 0.0676 1.0000
8.500 0.9847 0.02712 0.01791 -0.0134 0.0620 1.0000
8.750 1.0035 0.02822 0.01928 -0.0121 0.0560 1.0000
9.000 1.0197 0.02948 0.02060 -0.0108 0.0514 1.0000
9.250 1.0362 0.03084 0.02217 -0.0095 0.0461 1.0000
9.500 1.0510 0.03199 0.02344 -0.0081 0.0413 1.0000
9.750 1.0637 0.03355 0.02514 -0.0066 0.0373 1.0000
10.000 1.0769 0.03528 0.02715 -0.0049 0.0339 1.0000
10.250 1.0872 0.03687 0.02887 -0.0032 0.0313 1.0000
10.500 1.0931 0.03884 0.03089 -0.0013 0.0290 1.0000
10.750 1.0983 0.04088 0.03336 0.0010 0.0269 1.0000
11.000 1.1005 0.04300 0.03574 0.0033 0.0252 1.0000
11.250 1.1002 0.04529 0.03825 0.0053 0.0240 1.0000
11.500 1.0984 0.04769 0.04082 0.0071 0.0232 1.0000
11.750 1.0945 0.05035 0.04364 0.0084 0.0226 1.0000
12.000 1.0881 0.05346 0.04690 0.0093 0.0221 1.0000
12.500 1.0628 0.06186 0.05578 0.0088 0.0215 1.0000
12.750 1.0471 0.06693 0.06110 0.0070 0.0214 1.0000
13.000 1.0294 0.07282 0.06722 0.0042 0.0214 1.0000
13.250 1.0104 0.07949 0.07409 0.0003 0.0215 1.0000
13.500 0.9886 0.08740 0.08219 -0.0049 0.0216 1.0000
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Polar data table (+)
Polar graphs
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