RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 500,000 Max Cl/Cd: 81.85 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg149-il-500000.txt Download as CSV file: xf-rg149-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5274 0.08490 0.08261 -0.0254 1.0000 0.0223
-9.250 -0.5325 0.08011 0.07785 -0.0280 1.0000 0.0229
-9.000 -0.5420 0.07443 0.07222 -0.0317 1.0000 0.0233
-8.750 -0.6955 0.03996 0.03683 -0.0419 1.0000 0.0146
-8.500 -0.7014 0.03585 0.03237 -0.0391 1.0000 0.0145
-8.250 -0.6987 0.03276 0.02894 -0.0365 1.0000 0.0144
-8.000 -0.6979 0.02888 0.02466 -0.0336 1.0000 0.0145
-7.750 -0.6919 0.02560 0.02105 -0.0311 1.0000 0.0149
-7.500 -0.6750 0.02503 0.02048 -0.0298 1.0000 0.0156
-7.250 -0.6578 0.02431 0.01970 -0.0283 1.0000 0.0164
-7.000 -0.6421 0.02296 0.01814 -0.0265 1.0000 0.0173
-6.750 -0.6267 0.02102 0.01590 -0.0245 1.0000 0.0179
-6.500 -0.6091 0.01957 0.01419 -0.0227 1.0000 0.0185
-6.250 -0.5900 0.01860 0.01302 -0.0211 1.0000 0.0190
-6.000 -0.5687 0.01678 0.01094 -0.0201 0.9996 0.0198
-5.750 -0.5362 0.01532 0.00940 -0.0216 0.9975 0.0217
-5.500 -0.5006 0.01474 0.00877 -0.0235 0.9952 0.0235
-5.250 -0.4662 0.01396 0.00789 -0.0249 0.9928 0.0249
-5.000 -0.4317 0.01343 0.00727 -0.0264 0.9896 0.0260
-4.750 -0.3987 0.01217 0.00592 -0.0277 0.9867 0.0285
-4.500 -0.3621 0.01163 0.00536 -0.0297 0.9844 0.0307
-4.250 -0.3281 0.01116 0.00485 -0.0310 0.9808 0.0330
-4.000 -0.2943 0.01068 0.00432 -0.0323 0.9764 0.0359
-3.750 -0.2579 0.01019 0.00383 -0.0341 0.9732 0.0427
-3.500 -0.2202 0.00961 0.00336 -0.0363 0.9709 0.0685
-3.250 -0.1898 0.00910 0.00307 -0.0370 0.9648 0.1166
-3.000 -0.1545 0.00861 0.00282 -0.0387 0.9609 0.1765
-2.750 -0.1173 0.00810 0.00260 -0.0410 0.9581 0.2519
-2.500 -0.0869 0.00759 0.00240 -0.0417 0.9515 0.3383
-2.250 -0.0556 0.00691 0.00219 -0.0426 0.9453 0.4692
-2.000 -0.0288 0.00619 0.00204 -0.0425 0.9367 0.6236
-1.750 -0.0005 0.00572 0.00203 -0.0422 0.9288 0.7550
-1.500 0.0267 0.00561 0.00201 -0.0415 0.9171 0.8058
-1.250 0.0547 0.00556 0.00196 -0.0411 0.9049 0.8344
-1.000 0.0817 0.00553 0.00194 -0.0404 0.8915 0.8589
-0.750 0.1077 0.00553 0.00192 -0.0395 0.8769 0.8782
-0.500 0.1332 0.00555 0.00190 -0.0385 0.8612 0.8935
-0.250 0.1584 0.00558 0.00187 -0.0375 0.8445 0.9068
0.000 0.1830 0.00563 0.00186 -0.0363 0.8260 0.9193
0.250 0.2073 0.00568 0.00185 -0.0351 0.8055 0.9316
0.500 0.2319 0.00576 0.00184 -0.0340 0.7850 0.9430
0.750 0.2595 0.00584 0.00184 -0.0336 0.7623 0.9518
1.000 0.2889 0.00595 0.00185 -0.0336 0.7405 0.9604
1.250 0.3206 0.00606 0.00189 -0.0342 0.7186 0.9689
1.500 0.3566 0.00619 0.00192 -0.0358 0.6942 0.9738
1.750 0.3942 0.00634 0.00195 -0.0378 0.6661 0.9781
2.000 0.4294 0.00650 0.00201 -0.0393 0.6387 0.9836
2.250 0.4688 0.00665 0.00205 -0.0418 0.6098 0.9869
2.500 0.5049 0.00683 0.00209 -0.0437 0.5738 0.9912
2.750 0.5395 0.00702 0.00215 -0.0453 0.5382 0.9952
3.000 0.5750 0.00721 0.00221 -0.0471 0.5032 0.9987
3.250 0.6008 0.00739 0.00228 -0.0469 0.4702 1.0000
3.500 0.6193 0.00759 0.00238 -0.0452 0.4398 1.0000
3.750 0.6376 0.00779 0.00249 -0.0434 0.4108 1.0000
4.000 0.6556 0.00804 0.00262 -0.0415 0.3788 1.0000
4.250 0.6739 0.00833 0.00277 -0.0398 0.3432 1.0000
4.500 0.6928 0.00867 0.00296 -0.0381 0.3054 1.0000
4.750 0.7122 0.00909 0.00319 -0.0366 0.2616 1.0000
5.000 0.7323 0.00955 0.00346 -0.0353 0.2168 1.0000
5.250 0.7533 0.01003 0.00375 -0.0342 0.1781 1.0000
5.500 0.7755 0.01045 0.00406 -0.0332 0.1543 1.0000
5.750 0.7982 0.01088 0.00441 -0.0324 0.1350 1.0000
6.000 0.8218 0.01123 0.00473 -0.0317 0.1174 1.0000
6.250 0.8451 0.01163 0.00506 -0.0310 0.1000 1.0000
6.500 0.8682 0.01207 0.00543 -0.0302 0.0854 1.0000
6.750 0.8913 0.01251 0.00586 -0.0295 0.0739 1.0000
7.000 0.9144 0.01297 0.00630 -0.0287 0.0640 1.0000
7.250 0.9367 0.01350 0.00680 -0.0279 0.0549 1.0000
7.500 0.9598 0.01394 0.00724 -0.0272 0.0479 1.0000
7.750 0.9824 0.01444 0.00777 -0.0264 0.0421 1.0000
8.000 1.0044 0.01499 0.00833 -0.0255 0.0367 1.0000
8.250 1.0262 0.01556 0.00896 -0.0246 0.0326 1.0000
8.500 1.0480 0.01612 0.00952 -0.0237 0.0284 1.0000
8.750 1.0683 0.01682 0.01028 -0.0226 0.0244 1.0000
9.000 1.0887 0.01748 0.01095 -0.0216 0.0210 1.0000
9.250 1.1058 0.01849 0.01207 -0.0200 0.0185 1.0000
9.500 1.1253 0.01921 0.01287 -0.0188 0.0168 1.0000
9.750 1.1429 0.02008 0.01379 -0.0174 0.0154 1.0000
10.000 1.1518 0.02180 0.01563 -0.0149 0.0142 1.0000
10.250 1.1703 0.02251 0.01645 -0.0136 0.0134 1.0000
10.500 1.1861 0.02342 0.01747 -0.0120 0.0126 1.0000
10.750 1.2016 0.02424 0.01837 -0.0105 0.0118 1.0000
11.000 1.2131 0.02526 0.01947 -0.0084 0.0113 1.0000
11.250 1.2193 0.02655 0.02087 -0.0057 0.0109 1.0000
11.500 1.2143 0.02897 0.02346 -0.0018 0.0104 1.0000
11.750 1.2178 0.03063 0.02528 0.0008 0.0102 1.0000
12.000 1.2224 0.03211 0.02693 0.0030 0.0100 1.0000
12.250 1.2244 0.03388 0.02887 0.0052 0.0099 1.0000
12.500 1.2238 0.03598 0.03115 0.0071 0.0097 1.0000
12.750 1.2224 0.03821 0.03356 0.0086 0.0095 1.0000
13.000 1.2179 0.04093 0.03646 0.0098 0.0093 1.0000
13.250 1.2105 0.04417 0.03990 0.0103 0.0093 1.0000
13.500 1.2031 0.04763 0.04353 0.0102 0.0091 1.0000
13.750 1.1947 0.05149 0.04756 0.0094 0.0090 1.0000
14.000 1.1801 0.05660 0.05288 0.0077 0.0090 1.0000
14.250 1.1686 0.06163 0.05808 0.0054 0.0089 1.0000
14.500 1.1523 0.06788 0.06452 0.0021 0.0089 1.0000
14.750 1.1308 0.07553 0.07237 -0.0023 0.0091 1.0000
15.000 1.1124 0.08321 0.08022 -0.0071 0.0090 1.0000
15.250 1.0894 0.09235 0.08953 -0.0129 0.0091 1.0000
15.500 1.0620 0.10316 0.10052 -0.0197 0.0092 1.0000
15.750 1.0334 0.11487 0.11239 -0.0269 0.0095 1.0000
16.000 0.9980 0.12922 0.12689 -0.0355 0.0098 1.0000
16.250 0.9111 0.16141 0.15925 -0.0526 0.0108 1.0000
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