RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 50,000 Max Cl/Cd: 32.33 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a111-il-50000.txt Download as CSV file: xf-rg15a111-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4176 0.09731 0.09030 -0.0129 1.0000 0.3262
-8.250 -0.4125 0.09402 0.08705 -0.0120 1.0000 0.3390
-7.750 -0.5367 0.07353 0.06703 -0.0367 1.0000 0.1643
-7.500 -0.5817 0.06431 0.05737 -0.0416 1.0000 0.1376
-7.250 -0.5728 0.06008 0.05317 -0.0405 1.0000 0.1353
-7.000 -0.5719 0.05549 0.04840 -0.0397 1.0000 0.1312
-6.750 -0.5814 0.04953 0.04147 -0.0395 1.0000 0.1233
-6.500 -0.5709 0.04563 0.03728 -0.0382 1.0000 0.1225
-6.250 -0.5597 0.04202 0.03315 -0.0369 1.0000 0.1230
-6.000 -0.5439 0.03937 0.03056 -0.0356 1.0000 0.1285
-5.750 -0.5278 0.03663 0.02740 -0.0343 1.0000 0.1337
-5.500 -0.5092 0.03374 0.02383 -0.0330 1.0000 0.1381
-5.250 -0.4896 0.03163 0.02169 -0.0317 1.0000 0.1485
-5.000 -0.4693 0.02965 0.01951 -0.0304 1.0000 0.1637
-4.750 -0.4484 0.02776 0.01755 -0.0291 1.0000 0.1845
-4.500 -0.4287 0.02624 0.01616 -0.0277 1.0000 0.2169
-4.250 -0.4092 0.02482 0.01491 -0.0262 1.0000 0.2599
-4.000 -0.3894 0.02343 0.01373 -0.0246 1.0000 0.3130
-3.750 -0.3704 0.02200 0.01278 -0.0227 1.0000 0.3859
-3.500 -0.3552 0.02069 0.01231 -0.0197 1.0000 0.4977
-3.250 -0.3483 0.02042 0.01281 -0.0136 1.0000 0.6294
-3.000 -0.3460 0.02069 0.01335 -0.0060 1.0000 0.7280
-2.750 -0.3452 0.02091 0.01364 0.0018 1.0000 0.8026
-2.500 -0.3363 0.02109 0.01375 0.0084 1.0000 0.8742
-2.250 -0.0686 0.02222 0.01342 -0.0297 1.0000 1.0000
-2.000 -0.0802 0.02187 0.01304 -0.0257 1.0000 1.0000
-1.750 -0.0922 0.02156 0.01269 -0.0215 1.0000 1.0000
-1.500 -0.1044 0.02126 0.01235 -0.0172 1.0000 1.0000
-1.250 -0.1155 0.02096 0.01199 -0.0130 1.0000 1.0000
-1.000 -0.1218 0.02075 0.01168 -0.0095 1.0000 1.0000
-0.750 -0.1180 0.02072 0.01152 -0.0075 1.0000 1.0000
-0.500 -0.1066 0.02088 0.01151 -0.0066 1.0000 1.0000
-0.250 -0.0918 0.02117 0.01164 -0.0062 1.0000 1.0000
0.000 -0.0755 0.02155 0.01188 -0.0060 1.0000 1.0000
0.250 -0.0585 0.02201 0.01219 -0.0060 1.0000 1.0000
0.500 -0.0414 0.02255 0.01261 -0.0060 1.0000 1.0000
0.750 -0.0199 0.02324 0.01320 -0.0070 0.9981 1.0000
1.000 0.0369 0.02468 0.01451 -0.0142 0.9804 1.0000
1.250 0.0878 0.02581 0.01558 -0.0201 0.9619 1.0000
1.500 0.1402 0.02689 0.01661 -0.0260 0.9440 1.0000
1.750 0.1855 0.02774 0.01742 -0.0303 0.9249 1.0000
2.000 0.2297 0.02848 0.01816 -0.0342 0.9052 1.0000
2.250 0.2786 0.02915 0.01887 -0.0386 0.8862 1.0000
2.500 0.3215 0.02971 0.01947 -0.0417 0.8666 1.0000
2.750 0.3610 0.03019 0.02001 -0.0441 0.8460 1.0000
3.000 0.4111 0.03042 0.02034 -0.0476 0.8269 1.0000
3.250 0.4526 0.03064 0.02066 -0.0496 0.8066 1.0000
3.500 0.4958 0.03068 0.02084 -0.0515 0.7858 1.0000
3.750 0.5516 0.03018 0.02051 -0.0545 0.7670 1.0000
4.000 0.5864 0.03016 0.02063 -0.0546 0.7449 1.0000
4.250 0.6319 0.02959 0.02021 -0.0555 0.7240 1.0000
4.500 0.6687 0.02925 0.02000 -0.0552 0.7011 1.0000
4.750 0.7112 0.02853 0.01942 -0.0551 0.6781 1.0000
5.000 0.7407 0.02840 0.01940 -0.0538 0.6521 1.0000
5.250 0.7731 0.02811 0.01918 -0.0526 0.6257 1.0000
5.500 0.8047 0.02786 0.01899 -0.0512 0.5980 1.0000
5.750 0.8332 0.02779 0.01894 -0.0496 0.5685 1.0000
6.000 0.8590 0.02789 0.01904 -0.0478 0.5378 1.0000
6.250 0.8836 0.02812 0.01925 -0.0459 0.5058 1.0000
6.500 0.9077 0.02843 0.01951 -0.0440 0.4730 1.0000
6.750 0.9321 0.02883 0.01978 -0.0422 0.4399 1.0000
7.000 0.9520 0.02956 0.02045 -0.0401 0.4067 1.0000
7.250 0.9708 0.03045 0.02131 -0.0381 0.3739 1.0000
7.500 0.9899 0.03148 0.02229 -0.0361 0.3424 1.0000
7.750 1.0085 0.03262 0.02336 -0.0342 0.3121 1.0000
8.000 1.0265 0.03399 0.02468 -0.0323 0.2842 1.0000
8.250 1.0445 0.03544 0.02606 -0.0306 0.2582 1.0000
8.500 1.0645 0.03693 0.02739 -0.0292 0.2341 1.0000
8.750 1.0773 0.03899 0.02968 -0.0271 0.2143 1.0000
9.000 1.0919 0.04097 0.03177 -0.0252 0.1960 1.0000
9.250 1.1065 0.04347 0.03442 -0.0235 0.1816 1.0000
9.500 1.1175 0.04606 0.03722 -0.0216 0.1690 1.0000
9.750 1.1293 0.04895 0.04028 -0.0199 0.1588 1.0000
10.000 1.1421 0.05182 0.04330 -0.0183 0.1498 1.0000
10.250 1.1362 0.05559 0.04752 -0.0155 0.1448 1.0000
10.500 1.1262 0.05933 0.05167 -0.0126 0.1407 1.0000
10.750 1.1450 0.06275 0.05506 -0.0121 0.1338 1.0000
11.000 1.1240 0.06713 0.05981 -0.0091 0.1332 1.0000
11.250 1.1000 0.07149 0.06444 -0.0065 0.1331 1.0000
11.500 1.0744 0.07615 0.06927 -0.0046 0.1335 1.0000
11.750 1.0488 0.08146 0.07473 -0.0042 0.1340 1.0000
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Polar data table (+)
Polar graphs
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