R140 (original) (r140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 200,000 Max Cl/Cd: 48.64 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140-il-200000.txt Download as CSV file: xf-r140-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: R140 (original)
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5790 0.08536 0.08182 -0.0465 1.0000 0.0408
-10.000 -0.5977 0.08121 0.07760 -0.0483 1.0000 0.0408
-9.750 -0.6163 0.07794 0.07425 -0.0483 1.0000 0.0409
-9.500 -0.6358 0.07535 0.07157 -0.0464 1.0000 0.0409
-9.250 -0.6553 0.07325 0.06938 -0.0428 1.0000 0.0410
-7.000 -0.7103 0.03686 0.03118 -0.0096 1.0000 0.0179
-6.750 -0.7106 0.03360 0.02760 -0.0052 1.0000 0.0170
-6.500 -0.7060 0.03060 0.02425 -0.0011 1.0000 0.0161
-6.250 -0.6968 0.02802 0.02133 0.0023 1.0000 0.0152
-6.000 -0.6839 0.02545 0.01842 0.0054 1.0000 0.0146
-5.750 -0.6684 0.02320 0.01588 0.0080 1.0000 0.0140
-5.250 -0.6087 0.01930 0.01158 0.0072 0.9938 0.0145
-5.000 -0.5758 0.01790 0.01004 0.0059 0.9873 0.0155
-4.750 -0.5382 0.01686 0.00881 0.0035 0.9819 0.0186
-4.500 -0.5058 0.01586 0.00786 0.0022 0.9737 0.0350
-4.250 -0.4682 0.01487 0.00692 -0.0002 0.9686 0.0766
-4.000 -0.4356 0.01423 0.00638 -0.0017 0.9601 0.1194
-3.750 -0.4182 0.01203 0.00566 -0.0013 0.9517 0.4265
-3.500 -0.3903 0.01135 0.00557 -0.0014 0.9442 0.5756
-3.250 -0.3572 0.01119 0.00543 -0.0024 0.9363 0.6274
-3.000 -0.3234 0.01096 0.00533 -0.0032 0.9299 0.6867
-2.750 -0.2928 0.01079 0.00520 -0.0034 0.9205 0.7147
-2.500 -0.2554 0.01067 0.00506 -0.0051 0.9144 0.7345
-2.250 -0.2247 0.01060 0.00494 -0.0054 0.9050 0.7533
-2.000 -0.1932 0.01055 0.00488 -0.0059 0.8958 0.7693
-1.750 -0.1600 0.01050 0.00475 -0.0067 0.8879 0.7841
-1.500 -0.1332 0.01052 0.00473 -0.0061 0.8768 0.8019
-1.250 -0.1091 0.01054 0.00473 -0.0049 0.8647 0.8198
-1.000 -0.0815 0.01056 0.00476 -0.0045 0.8538 0.8342
-0.750 -0.0534 0.01056 0.00473 -0.0043 0.8441 0.8471
-0.500 -0.0216 0.01055 0.00466 -0.0049 0.8362 0.8578
-0.250 0.0091 0.01059 0.00469 -0.0053 0.8268 0.8683
0.000 0.0412 0.01066 0.00472 -0.0060 0.8186 0.8784
0.250 0.0734 0.01075 0.00477 -0.0067 0.8104 0.8888
0.500 0.1073 0.01091 0.00493 -0.0079 0.7999 0.8975
0.750 0.1421 0.01105 0.00506 -0.0093 0.7896 0.9051
1.000 0.1734 0.01116 0.00515 -0.0100 0.7801 0.9148
1.250 0.2157 0.01130 0.00528 -0.0129 0.7711 0.9194
1.500 0.2492 0.01140 0.00543 -0.0141 0.7612 0.9287
1.750 0.2943 0.01152 0.00556 -0.0177 0.7519 0.9323
2.000 0.3275 0.01161 0.00564 -0.0188 0.7410 0.9413
2.250 0.3717 0.01170 0.00577 -0.0222 0.7297 0.9445
2.500 0.4103 0.01180 0.00593 -0.0245 0.7176 0.9507
2.750 0.4478 0.01186 0.00603 -0.0266 0.7038 0.9575
3.000 0.4812 0.01175 0.00577 -0.0272 0.6602 0.9650
3.250 0.5153 0.01169 0.00559 -0.0283 0.6040 0.9724
3.500 0.5508 0.01182 0.00574 -0.0300 0.5666 0.9804
3.750 0.5866 0.01206 0.00569 -0.0318 0.4662 0.9870
4.000 0.6000 0.01469 0.00647 -0.0312 0.0958 0.9958
4.250 0.6265 0.01582 0.00724 -0.0317 0.0228 1.0000
4.500 0.6398 0.01628 0.00784 -0.0292 0.0199 1.0000
4.750 0.6522 0.01680 0.00849 -0.0265 0.0188 1.0000
5.000 0.6619 0.01751 0.00932 -0.0232 0.0177 1.0000
5.250 0.6704 0.01825 0.01016 -0.0198 0.0173 1.0000
5.500 0.6779 0.01912 0.01110 -0.0162 0.0171 1.0000
5.750 0.6857 0.02010 0.01216 -0.0125 0.0171 1.0000
6.000 0.6960 0.02129 0.01343 -0.0092 0.0173 1.0000
6.250 0.7110 0.02280 0.01511 -0.0066 0.0176 1.0000
6.500 0.7310 0.02471 0.01719 -0.0048 0.0184 1.0000
6.750 0.7529 0.02737 0.02015 -0.0030 0.0197 1.0000
7.000 0.7702 0.03032 0.02343 -0.0007 0.0213 1.0000
7.250 0.7814 0.03403 0.02746 0.0023 0.0231 1.0000
8.750 0.7943 0.05539 0.05096 0.0267 0.0435 1.0000
9.000 0.7854 0.05795 0.05372 0.0306 0.0416 1.0000
9.250 0.7755 0.06055 0.05646 0.0340 0.0407 1.0000
9.500 0.7624 0.06299 0.05899 0.0376 0.0397 1.0000
9.750 0.7440 0.06549 0.06160 0.0411 0.0397 1.0000
10.000 0.7263 0.06841 0.06461 0.0431 0.0394 1.0000
10.250 0.7077 0.07186 0.06816 0.0437 0.0392 1.0000
10.500 0.6877 0.07612 0.07250 0.0430 0.0389 1.0000
10.750 0.6645 0.08143 0.07791 0.0401 0.0393 1.0000
11.000 0.6406 0.08863 0.08516 0.0353 0.0396 1.0000
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Polar data table (+)
Polar graphs
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