RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.01 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg149-il-1000000.txt Download as CSV file: xf-rg149-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7938 0.04468 0.04271 -0.0538 1.0000 0.0073
-11.000 -0.8438 0.03895 0.03674 -0.0516 1.0000 0.0071
-10.750 -0.8588 0.03544 0.03298 -0.0489 1.0000 0.0072
-10.500 -0.8643 0.03251 0.02979 -0.0462 1.0000 0.0072
-10.250 -0.8624 0.03022 0.02726 -0.0438 1.0000 0.0073
-10.000 -0.8860 0.02404 0.02038 -0.0388 1.0000 0.0076
-9.750 -0.8751 0.02240 0.01856 -0.0367 1.0000 0.0078
-9.500 -0.8577 0.02173 0.01784 -0.0353 1.0000 0.0081
-9.250 -0.8395 0.02115 0.01720 -0.0339 1.0000 0.0083
-9.000 -0.8219 0.02040 0.01635 -0.0324 1.0000 0.0086
-8.750 -0.8056 0.01934 0.01514 -0.0306 1.0000 0.0088
-8.500 -0.7876 0.01856 0.01424 -0.0291 1.0000 0.0092
-8.250 -0.7704 0.01754 0.01307 -0.0274 1.0000 0.0095
-8.000 -0.7517 0.01681 0.01222 -0.0259 1.0000 0.0099
-7.750 -0.7253 0.01629 0.01160 -0.0259 0.9994 0.0102
-7.500 -0.6964 0.01449 0.00957 -0.0268 0.9978 0.0109
-7.250 -0.6634 0.01399 0.00905 -0.0283 0.9963 0.0116
-7.000 -0.6288 0.01383 0.00887 -0.0300 0.9950 0.0125
-6.750 -0.5954 0.01335 0.00833 -0.0313 0.9936 0.0133
-6.500 -0.5633 0.01304 0.00796 -0.0323 0.9914 0.0140
-6.250 -0.5330 0.01189 0.00669 -0.0331 0.9890 0.0149
-6.000 -0.5004 0.01121 0.00597 -0.0344 0.9870 0.0160
-5.750 -0.4660 0.01086 0.00561 -0.0360 0.9855 0.0172
-5.500 -0.4308 0.01055 0.00527 -0.0376 0.9842 0.0184
-5.250 -0.3974 0.01027 0.00497 -0.0389 0.9821 0.0192
-5.000 -0.3689 0.00954 0.00414 -0.0391 0.9778 0.0206
-4.750 -0.3356 0.00908 0.00366 -0.0403 0.9751 0.0224
-4.500 -0.3004 0.00875 0.00332 -0.0419 0.9730 0.0241
-4.250 -0.2645 0.00845 0.00299 -0.0437 0.9713 0.0256
-4.000 -0.2357 0.00812 0.00261 -0.0438 0.9657 0.0282
-3.750 -0.2044 0.00781 0.00233 -0.0444 0.9605 0.0337
-3.500 -0.1721 0.00740 0.00204 -0.0454 0.9558 0.0607
-3.250 -0.1438 0.00708 0.00184 -0.0455 0.9467 0.0906
-3.000 -0.1137 0.00679 0.00166 -0.0460 0.9377 0.1240
-2.750 -0.0843 0.00650 0.00149 -0.0464 0.9272 0.1664
-2.500 -0.0568 0.00620 0.00135 -0.0463 0.9139 0.2212
-2.250 -0.0305 0.00592 0.00123 -0.0460 0.8994 0.2830
-2.000 -0.0049 0.00562 0.00113 -0.0456 0.8841 0.3572
-1.750 0.0202 0.00530 0.00104 -0.0450 0.8681 0.4436
-1.500 0.0441 0.00489 0.00096 -0.0443 0.8513 0.5612
-1.250 0.0679 0.00457 0.00091 -0.0434 0.8339 0.6631
-1.000 0.0917 0.00437 0.00093 -0.0424 0.8150 0.7528
-0.750 0.1169 0.00436 0.00094 -0.0416 0.7937 0.7934
-0.500 0.1424 0.00439 0.00096 -0.0408 0.7724 0.8222
-0.250 0.1683 0.00446 0.00097 -0.0402 0.7514 0.8404
0.000 0.1942 0.00453 0.00098 -0.0396 0.7277 0.8540
0.250 0.2201 0.00460 0.00099 -0.0390 0.7058 0.8658
0.500 0.2459 0.00468 0.00102 -0.0384 0.6843 0.8768
0.750 0.2718 0.00476 0.00105 -0.0378 0.6643 0.8880
1.000 0.2977 0.00485 0.00108 -0.0372 0.6416 0.8982
1.250 0.3228 0.00496 0.00112 -0.0365 0.6149 0.9068
1.500 0.3483 0.00507 0.00116 -0.0359 0.5915 0.9159
1.750 0.3733 0.00518 0.00121 -0.0351 0.5685 0.9261
2.000 0.3977 0.00530 0.00127 -0.0342 0.5431 0.9358
2.250 0.4220 0.00546 0.00133 -0.0333 0.5107 0.9452
2.500 0.4462 0.00563 0.00140 -0.0324 0.4803 0.9558
2.750 0.4726 0.00579 0.00148 -0.0320 0.4520 0.9659
3.000 0.5019 0.00600 0.00158 -0.0323 0.4207 0.9748
3.250 0.5324 0.00622 0.00169 -0.0330 0.3899 0.9829
3.500 0.5674 0.00645 0.00181 -0.0347 0.3582 0.9864
3.750 0.6013 0.00675 0.00196 -0.0362 0.3191 0.9896
4.000 0.6337 0.00704 0.00211 -0.0374 0.2818 0.9932
4.250 0.6662 0.00744 0.00229 -0.0387 0.2348 0.9961
4.500 0.6986 0.00788 0.00251 -0.0401 0.1857 0.9992
4.750 0.7202 0.00820 0.00272 -0.0391 0.1593 1.0000
5.000 0.7403 0.00846 0.00291 -0.0376 0.1431 1.0000
5.250 0.7624 0.00871 0.00310 -0.0365 0.1298 1.0000
5.500 0.7856 0.00896 0.00331 -0.0357 0.1154 1.0000
5.750 0.8091 0.00926 0.00354 -0.0349 0.0988 1.0000
6.000 0.8327 0.00960 0.00379 -0.0342 0.0837 1.0000
6.250 0.8567 0.00992 0.00406 -0.0336 0.0718 1.0000
6.500 0.8810 0.01023 0.00434 -0.0330 0.0618 1.0000
6.750 0.9054 0.01055 0.00464 -0.0324 0.0536 1.0000
7.000 0.9291 0.01094 0.00497 -0.0318 0.0449 1.0000
7.250 0.9538 0.01122 0.00526 -0.0313 0.0402 1.0000
7.500 0.9776 0.01161 0.00563 -0.0307 0.0342 1.0000
7.750 1.0018 0.01195 0.00596 -0.0301 0.0302 1.0000
8.000 1.0251 0.01239 0.00641 -0.0294 0.0259 1.0000
8.250 1.0492 0.01271 0.00675 -0.0289 0.0232 1.0000
8.500 1.0715 0.01325 0.00728 -0.0281 0.0193 1.0000
8.750 1.0951 0.01362 0.00767 -0.0275 0.0168 1.0000
9.000 1.1165 0.01423 0.00831 -0.0265 0.0138 1.0000
9.250 1.1392 0.01468 0.00879 -0.0258 0.0120 1.0000
9.500 1.1588 0.01547 0.00961 -0.0245 0.0102 1.0000
9.750 1.1811 0.01591 0.01011 -0.0238 0.0096 1.0000
10.000 1.2022 0.01647 0.01073 -0.0228 0.0089 1.0000
10.250 1.2225 0.01708 0.01139 -0.0218 0.0083 1.0000
10.500 1.2386 0.01810 0.01249 -0.0202 0.0075 1.0000
10.750 1.2546 0.01904 0.01356 -0.0185 0.0072 1.0000
11.000 1.2723 0.01978 0.01439 -0.0171 0.0070 1.0000
11.250 1.2892 0.02053 0.01523 -0.0157 0.0068 1.0000
11.500 1.3053 0.02130 0.01608 -0.0142 0.0065 1.0000
11.750 1.3186 0.02222 0.01710 -0.0123 0.0063 1.0000
12.000 1.3291 0.02311 0.01808 -0.0099 0.0061 1.0000
12.250 1.3375 0.02402 0.01907 -0.0072 0.0059 1.0000
12.500 1.3435 0.02507 0.02022 -0.0044 0.0057 1.0000
12.750 1.3488 0.02620 0.02144 -0.0018 0.0056 1.0000
13.000 1.3495 0.02768 0.02305 0.0010 0.0054 1.0000
13.250 1.3493 0.02931 0.02479 0.0036 0.0054 1.0000
13.500 1.3391 0.03185 0.02749 0.0063 0.0052 1.0000
13.750 1.3200 0.03548 0.03135 0.0085 0.0050 1.0000
14.000 1.3139 0.03832 0.03432 0.0094 0.0051 1.0000
14.250 1.3025 0.04204 0.03822 0.0095 0.0050 1.0000
14.500 1.3058 0.04440 0.04068 0.0092 0.0049 1.0000
14.750 1.2791 0.05079 0.04728 0.0074 0.0050 1.0000
15.000 1.2872 0.05303 0.04960 0.0064 0.0048 1.0000
15.250 1.2761 0.05815 0.05486 0.0040 0.0048 1.0000
15.500 1.2558 0.06512 0.06201 0.0004 0.0048 1.0000
15.750 1.2519 0.06977 0.06675 -0.0022 0.0048 1.0000
16.000 1.2314 0.07753 0.07467 -0.0067 0.0048 1.0000
16.250 1.2112 0.08571 0.08299 -0.0115 0.0048 1.0000
16.500 1.1819 0.09594 0.09338 -0.0174 0.0048 1.0000
16.750 1.1502 0.10726 0.10487 -0.0240 0.0049 1.0000
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