RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.45 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1495-il-1000000.txt Download as CSV file: xf-rg1495-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8873 0.04350 0.04127 -0.0587 1.0000 0.0077
-12.250 -0.9130 0.03855 0.03612 -0.0600 1.0000 0.0077
-12.000 -0.9369 0.03536 0.03274 -0.0572 1.0000 0.0076
-11.750 -0.9490 0.03329 0.03051 -0.0533 1.0000 0.0077
-11.500 -0.9602 0.03035 0.02729 -0.0498 1.0000 0.0077
-11.250 -0.9518 0.02915 0.02597 -0.0477 1.0000 0.0079
-11.000 -0.9460 0.02751 0.02416 -0.0452 1.0000 0.0081
-10.750 -0.9365 0.02616 0.02266 -0.0431 1.0000 0.0083
-10.500 -0.9265 0.02475 0.02108 -0.0408 1.0000 0.0085
-10.250 -0.9158 0.02332 0.01947 -0.0386 1.0000 0.0087
-10.000 -0.9026 0.02214 0.01813 -0.0366 1.0000 0.0089
-9.750 -0.8865 0.02132 0.01718 -0.0349 1.0000 0.0091
-9.500 -0.8688 0.02072 0.01647 -0.0333 1.0000 0.0093
-9.250 -0.8628 0.01818 0.01363 -0.0303 1.0000 0.0099
-9.000 -0.8446 0.01761 0.01301 -0.0288 1.0000 0.0102
-8.750 -0.8256 0.01714 0.01249 -0.0274 1.0000 0.0105
-8.500 -0.8061 0.01676 0.01208 -0.0260 1.0000 0.0110
-8.250 -0.7788 0.01633 0.01159 -0.0262 0.9993 0.0115
-8.000 -0.7461 0.01584 0.01102 -0.0275 0.9979 0.0121
-7.750 -0.7126 0.01552 0.01060 -0.0290 0.9964 0.0125
-7.500 -0.6831 0.01381 0.00872 -0.0300 0.9949 0.0135
-7.250 -0.6503 0.01333 0.00822 -0.0314 0.9934 0.0142
-7.000 -0.6186 0.01293 0.00780 -0.0324 0.9912 0.0151
-6.750 -0.5861 0.01247 0.00728 -0.0335 0.9890 0.0159
-6.500 -0.5519 0.01224 0.00702 -0.0350 0.9871 0.0166
-6.250 -0.5197 0.01130 0.00598 -0.0362 0.9854 0.0178
-6.000 -0.4856 0.01075 0.00541 -0.0378 0.9841 0.0190
-5.750 -0.4538 0.01037 0.00500 -0.0387 0.9817 0.0200
-5.500 -0.4234 0.01003 0.00463 -0.0393 0.9779 0.0212
-5.250 -0.3898 0.00974 0.00431 -0.0405 0.9754 0.0221
-5.000 -0.3558 0.00917 0.00369 -0.0419 0.9733 0.0240
-4.750 -0.3202 0.00880 0.00330 -0.0436 0.9717 0.0262
-4.500 -0.2898 0.00852 0.00301 -0.0441 0.9671 0.0283
-4.250 -0.2594 0.00820 0.00268 -0.0446 0.9617 0.0325
-4.000 -0.2266 0.00782 0.00238 -0.0456 0.9577 0.0464
-3.750 -0.1987 0.00750 0.00216 -0.0456 0.9496 0.0701
-3.500 -0.1668 0.00719 0.00195 -0.0465 0.9431 0.0954
-3.250 -0.1387 0.00693 0.00178 -0.0466 0.9325 0.1243
-3.000 -0.1102 0.00668 0.00162 -0.0467 0.9214 0.1570
-2.750 -0.0829 0.00643 0.00147 -0.0466 0.9087 0.1978
-2.500 -0.0564 0.00619 0.00135 -0.0463 0.8949 0.2462
-2.250 -0.0308 0.00589 0.00124 -0.0458 0.8803 0.3132
-2.000 -0.0057 0.00559 0.00115 -0.0453 0.8653 0.3899
-1.750 0.0189 0.00526 0.00107 -0.0447 0.8497 0.4834
-1.500 0.0433 0.00496 0.00099 -0.0440 0.8336 0.5710
-1.250 0.0678 0.00472 0.00094 -0.0432 0.8166 0.6480
-1.000 0.0915 0.00451 0.00095 -0.0422 0.7988 0.7354
-0.750 0.1163 0.00448 0.00098 -0.0413 0.7777 0.7852
-0.500 0.1418 0.00453 0.00099 -0.0406 0.7544 0.8122
-0.250 0.1678 0.00458 0.00100 -0.0400 0.7349 0.8301
0.000 0.1941 0.00464 0.00102 -0.0394 0.7153 0.8440
0.250 0.2203 0.00472 0.00104 -0.0389 0.6948 0.8560
0.500 0.2464 0.00480 0.00106 -0.0384 0.6737 0.8674
0.750 0.2720 0.00488 0.00109 -0.0377 0.6513 0.8779
1.000 0.2978 0.00498 0.00113 -0.0371 0.6281 0.8876
1.250 0.3237 0.00509 0.00117 -0.0366 0.6061 0.8964
1.500 0.3493 0.00518 0.00121 -0.0360 0.5841 0.9046
1.750 0.3748 0.00530 0.00126 -0.0353 0.5611 0.9140
2.000 0.3997 0.00541 0.00133 -0.0346 0.5381 0.9231
2.250 0.4244 0.00556 0.00139 -0.0338 0.5090 0.9316
2.500 0.4487 0.00572 0.00146 -0.0329 0.4791 0.9406
2.750 0.4729 0.00588 0.00154 -0.0320 0.4514 0.9501
3.000 0.4978 0.00605 0.00163 -0.0313 0.4245 0.9604
3.250 0.5238 0.00624 0.00173 -0.0309 0.3973 0.9708
3.500 0.5557 0.00645 0.00184 -0.0318 0.3695 0.9773
3.750 0.5867 0.00671 0.00198 -0.0326 0.3370 0.9840
4.000 0.6209 0.00699 0.00212 -0.0341 0.3027 0.9870
4.250 0.6539 0.00731 0.00229 -0.0355 0.2659 0.9899
4.500 0.6853 0.00770 0.00249 -0.0366 0.2236 0.9936
4.750 0.7179 0.00813 0.00272 -0.0380 0.1793 0.9965
5.000 0.7507 0.00850 0.00296 -0.0393 0.1526 0.9994
5.250 0.7718 0.00873 0.00315 -0.0382 0.1402 1.0000
5.500 0.7923 0.00894 0.00333 -0.0367 0.1293 1.0000
5.750 0.8140 0.00920 0.00353 -0.0356 0.1156 1.0000
6.000 0.8365 0.00950 0.00375 -0.0347 0.0998 1.0000
6.250 0.8597 0.00981 0.00400 -0.0338 0.0866 1.0000
6.500 0.8834 0.01011 0.00427 -0.0331 0.0767 1.0000
6.750 0.9073 0.01042 0.00455 -0.0325 0.0675 1.0000
7.000 0.9310 0.01076 0.00484 -0.0318 0.0586 1.0000
7.250 0.9548 0.01110 0.00514 -0.0312 0.0516 1.0000
7.500 0.9791 0.01140 0.00546 -0.0306 0.0459 1.0000
7.750 1.0022 0.01181 0.00583 -0.0299 0.0392 1.0000
8.000 1.0264 0.01211 0.00615 -0.0293 0.0358 1.0000
8.250 1.0491 0.01257 0.00657 -0.0285 0.0305 1.0000
8.500 1.0730 0.01288 0.00693 -0.0280 0.0279 1.0000
8.750 1.0956 0.01333 0.00735 -0.0272 0.0245 1.0000
9.000 1.1184 0.01375 0.00780 -0.0264 0.0218 1.0000
9.250 1.1408 0.01419 0.00824 -0.0257 0.0190 1.0000
9.500 1.1621 0.01473 0.00881 -0.0247 0.0163 1.0000
9.750 1.1836 0.01523 0.00932 -0.0238 0.0142 1.0000
10.000 1.2034 0.01589 0.01003 -0.0226 0.0123 1.0000
10.250 1.2245 0.01638 0.01056 -0.0217 0.0113 1.0000
10.500 1.2441 0.01698 0.01118 -0.0206 0.0102 1.0000
10.750 1.2606 0.01785 0.01214 -0.0189 0.0092 1.0000
11.000 1.2799 0.01842 0.01277 -0.0178 0.0088 1.0000
11.250 1.2976 0.01907 0.01350 -0.0164 0.0084 1.0000
11.500 1.3147 0.01974 0.01423 -0.0150 0.0079 1.0000
11.750 1.3295 0.02052 0.01508 -0.0132 0.0076 1.0000
12.000 1.3385 0.02150 0.01615 -0.0106 0.0072 1.0000
12.250 1.3358 0.02304 0.01783 -0.0062 0.0067 1.0000
12.500 1.3455 0.02386 0.01874 -0.0039 0.0066 1.0000
12.750 1.3538 0.02479 0.01976 -0.0016 0.0065 1.0000
13.000 1.3594 0.02593 0.02100 0.0009 0.0064 1.0000
13.250 1.3667 0.02701 0.02218 0.0029 0.0062 1.0000
13.500 1.3675 0.02858 0.02386 0.0053 0.0062 1.0000
13.750 1.3693 0.03019 0.02558 0.0072 0.0061 1.0000
14.000 1.3725 0.03180 0.02731 0.0087 0.0059 1.0000
14.250 1.3711 0.03393 0.02955 0.0100 0.0058 1.0000
14.500 1.3691 0.03630 0.03204 0.0110 0.0057 1.0000
14.750 1.3660 0.03897 0.03483 0.0114 0.0057 1.0000
15.000 1.3632 0.04185 0.03781 0.0114 0.0055 1.0000
15.250 1.3544 0.04568 0.04179 0.0107 0.0055 1.0000
15.500 1.3444 0.04999 0.04624 0.0095 0.0055 1.0000
15.750 1.3397 0.05390 0.05025 0.0079 0.0053 1.0000
16.000 1.3257 0.05941 0.05590 0.0054 0.0053 1.0000
16.250 1.3120 0.06524 0.06187 0.0025 0.0053 1.0000
16.500 1.2966 0.07167 0.06843 -0.0009 0.0052 1.0000
16.750 1.2764 0.07925 0.07616 -0.0051 0.0052 1.0000
17.000 1.2520 0.08796 0.08503 -0.0100 0.0053 1.0000
17.250 1.2307 0.09643 0.09364 -0.0148 0.0052 1.0000
17.500 1.2070 0.10561 0.10297 -0.0200 0.0054 1.0000
17.750 1.1831 0.11516 0.11265 -0.0255 0.0054 1.0000
18.000 1.1614 0.12456 0.12217 -0.0309 0.0054 1.0000
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