RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 200,000 Max Cl/Cd: 63.55 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg149-il-200000.txt Download as CSV file: xf-rg149-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5215 0.08892 0.08539 -0.0307 1.0000 0.0568
-9.000 -0.5406 0.08265 0.07916 -0.0382 1.0000 0.0571
-8.750 -0.5585 0.07867 0.07512 -0.0398 1.0000 0.0572
-8.500 -0.5728 0.07483 0.07116 -0.0406 1.0000 0.0573
-8.250 -0.5719 0.06807 0.06455 -0.0401 1.0000 0.0587
-8.000 -0.5629 0.06582 0.06236 -0.0382 1.0000 0.0599
-7.750 -0.5601 0.06306 0.05958 -0.0372 1.0000 0.0613
-7.500 -0.5603 0.05967 0.05612 -0.0368 1.0000 0.0629
-7.250 -0.5611 0.05591 0.05224 -0.0364 1.0000 0.0653
-7.000 -0.5788 0.05096 0.04657 -0.0355 1.0000 0.0711
-6.750 -0.5667 0.04710 0.04287 -0.0344 1.0000 0.0727
-6.500 -0.5704 0.03517 0.02998 -0.0308 1.0000 0.0424
-6.250 -0.5602 0.03162 0.02600 -0.0286 1.0000 0.0419
-6.000 -0.5474 0.02816 0.02209 -0.0264 1.0000 0.0411
-5.750 -0.5316 0.02495 0.01838 -0.0243 1.0000 0.0403
-5.500 -0.5129 0.02272 0.01577 -0.0226 1.0000 0.0407
-5.250 -0.4928 0.02130 0.01407 -0.0211 1.0000 0.0425
-5.000 -0.4719 0.02031 0.01282 -0.0196 1.0000 0.0446
-4.750 -0.4505 0.01923 0.01153 -0.0182 1.0000 0.0454
-4.500 -0.4292 0.01719 0.00938 -0.0171 1.0000 0.0476
-4.250 -0.4081 0.01644 0.00865 -0.0160 1.0000 0.0510
-4.000 -0.3866 0.01584 0.00798 -0.0148 1.0000 0.0551
-3.750 -0.3653 0.01508 0.00717 -0.0136 1.0000 0.0583
-3.500 -0.3449 0.01432 0.00648 -0.0125 1.0000 0.0648
-3.250 -0.3242 0.01375 0.00593 -0.0114 1.0000 0.0767
-3.000 -0.2986 0.01294 0.00536 -0.0114 0.9988 0.1196
-2.750 -0.2595 0.01213 0.00512 -0.0144 0.9937 0.2356
-2.500 -0.2233 0.01126 0.00501 -0.0169 0.9874 0.4089
-2.250 -0.1936 0.01021 0.00520 -0.0173 0.9815 0.6786
-2.000 -0.1647 0.01010 0.00552 -0.0163 0.9735 0.8338
-1.750 -0.1316 0.01017 0.00560 -0.0164 0.9660 0.8916
-1.500 -0.0899 0.01027 0.00565 -0.0182 0.9602 0.9314
-1.250 -0.0304 0.01045 0.00573 -0.0238 0.9590 0.9619
-1.000 0.0370 0.01054 0.00569 -0.0314 0.9590 0.9781
-0.750 0.1037 0.01048 0.00554 -0.0391 0.9583 0.9896
-0.500 0.1705 0.01031 0.00529 -0.0470 0.9574 0.9995
-0.250 0.2142 0.01008 0.00502 -0.0503 0.9477 1.0000
0.000 0.2598 0.00983 0.00474 -0.0539 0.9388 1.0000
0.250 0.3042 0.00956 0.00445 -0.0572 0.9285 1.0000
0.500 0.3418 0.00932 0.00419 -0.0590 0.9131 1.0000
0.750 0.3733 0.00913 0.00397 -0.0595 0.8925 1.0000
1.000 0.4039 0.00896 0.00374 -0.0597 0.8707 1.0000
1.250 0.4275 0.00888 0.00360 -0.0585 0.8446 1.0000
1.500 0.4500 0.00885 0.00350 -0.0571 0.8187 1.0000
1.750 0.4716 0.00885 0.00342 -0.0556 0.7923 1.0000
2.000 0.4927 0.00890 0.00338 -0.0539 0.7658 1.0000
2.250 0.5132 0.00898 0.00336 -0.0522 0.7391 1.0000
2.500 0.5333 0.00908 0.00338 -0.0505 0.7122 1.0000
2.750 0.5533 0.00921 0.00345 -0.0488 0.6851 1.0000
3.000 0.5730 0.00937 0.00351 -0.0470 0.6567 1.0000
3.250 0.5922 0.00956 0.00358 -0.0451 0.6257 1.0000
3.500 0.6115 0.00978 0.00368 -0.0432 0.5942 1.0000
3.750 0.6309 0.01000 0.00383 -0.0414 0.5618 1.0000
4.000 0.6506 0.01026 0.00398 -0.0397 0.5293 1.0000
4.250 0.6702 0.01055 0.00416 -0.0380 0.4950 1.0000
4.500 0.6901 0.01086 0.00436 -0.0364 0.4582 1.0000
4.750 0.7100 0.01123 0.00461 -0.0349 0.4188 1.0000
5.000 0.7297 0.01166 0.00488 -0.0333 0.3733 1.0000
5.250 0.7488 0.01220 0.00520 -0.0318 0.3205 1.0000
5.500 0.7675 0.01285 0.00560 -0.0303 0.2642 1.0000
5.750 0.7864 0.01359 0.00610 -0.0289 0.2158 1.0000
6.000 0.8059 0.01433 0.00665 -0.0276 0.1799 1.0000
6.250 0.8255 0.01512 0.00730 -0.0263 0.1535 1.0000
6.500 0.8448 0.01598 0.00804 -0.0250 0.1331 1.0000
6.750 0.8658 0.01666 0.00872 -0.0240 0.1157 1.0000
7.000 0.8867 0.01737 0.00943 -0.0229 0.1012 1.0000
7.250 0.9067 0.01824 0.01028 -0.0217 0.0896 1.0000
7.500 0.9260 0.01923 0.01123 -0.0204 0.0794 1.0000
7.750 0.9464 0.02003 0.01208 -0.0193 0.0705 1.0000
8.000 0.9662 0.02106 0.01319 -0.0181 0.0629 1.0000
8.250 0.9842 0.02245 0.01453 -0.0169 0.0558 1.0000
8.500 1.0050 0.02312 0.01540 -0.0158 0.0499 1.0000
8.750 1.0223 0.02493 0.01717 -0.0145 0.0445 1.0000
9.000 1.0417 0.02566 0.01812 -0.0133 0.0397 1.0000
9.250 1.0588 0.02712 0.01957 -0.0120 0.0358 1.0000
9.500 1.0760 0.02945 0.02217 -0.0106 0.0332 1.0000
9.750 1.0926 0.03106 0.02404 -0.0091 0.0308 1.0000
10.000 1.1075 0.03226 0.02534 -0.0077 0.0285 1.0000
10.250 1.1187 0.03535 0.02856 -0.0064 0.0266 1.0000
10.500 1.1256 0.03803 0.03162 -0.0041 0.0258 1.0000
10.750 1.1297 0.04057 0.03452 -0.0016 0.0251 1.0000
11.000 1.1280 0.04347 0.03779 0.0012 0.0248 1.0000
11.250 1.1191 0.04640 0.04103 0.0047 0.0245 1.0000
11.500 1.1058 0.04956 0.04449 0.0078 0.0244 1.0000
11.750 1.0899 0.05309 0.04829 0.0099 0.0244 1.0000
12.000 1.0705 0.05712 0.05257 0.0109 0.0244 1.0000
12.250 1.0505 0.06176 0.05744 0.0105 0.0245 1.0000
12.500 1.0275 0.06731 0.06321 0.0085 0.0246 1.0000
12.750 1.0048 0.07372 0.06981 0.0050 0.0249 1.0000
13.000 0.9806 0.08129 0.07754 0.0001 0.0251 1.0000
13.250 0.9561 0.08997 0.08635 -0.0059 0.0255 1.0000
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Polar data table (+)
Polar graphs
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