MRC-20 (mrc-20-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 500,000 Max Cl/Cd: 99.22 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-20-il-500000.txt Download as CSV file: xf-mrc-20-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MRC-20
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2717 0.08497 0.08260 -0.0883 0.9812 0.0199
-9.750 -0.2708 0.07804 0.07567 -0.0954 0.9783 0.0201
-9.500 -0.2769 0.06915 0.06671 -0.1067 0.9755 0.0202
-9.250 -0.2806 0.06254 0.05997 -0.1154 0.9734 0.0203
-9.000 -0.2942 0.05915 0.05647 -0.1153 0.9648 0.0205
-8.750 -0.2923 0.05476 0.05189 -0.1174 0.9613 0.0211
-8.500 -0.3162 0.05044 0.04695 -0.1125 0.9504 0.0220
-8.250 -0.3062 0.04602 0.04248 -0.1132 0.9479 0.0223
-8.000 -0.2900 0.04350 0.03990 -0.1138 0.9459 0.0225
-7.750 -0.2879 0.04195 0.03829 -0.1106 0.9379 0.0227
-7.500 -0.2725 0.03990 0.03613 -0.1102 0.9346 0.0231
-7.250 -0.2553 0.03772 0.03380 -0.1098 0.9321 0.0238
-7.000 -0.2531 0.03660 0.03202 -0.1041 0.9238 0.0262
-6.750 -0.2382 0.03250 0.02789 -0.1037 0.9204 0.0268
-6.500 -0.2165 0.03069 0.02604 -0.1036 0.9180 0.0273
-6.250 -0.1937 0.02910 0.02434 -0.1034 0.9159 0.0283
-6.000 -0.1859 0.02772 0.02242 -0.0990 0.9079 0.0316
-5.750 -0.1618 0.02568 0.02042 -0.0992 0.9049 0.0324
-5.500 -0.1363 0.02431 0.01899 -0.0992 0.9024 0.0337
-5.250 -0.1065 0.01897 0.01283 -0.0969 0.9005 0.0216
-5.000 -0.0868 0.01803 0.01175 -0.0952 0.8940 0.0218
-4.750 -0.0597 0.01675 0.01037 -0.0949 0.8904 0.0217
-4.500 -0.0310 0.01546 0.00903 -0.0950 0.8875 0.0214
-4.250 -0.0048 0.01456 0.00804 -0.0946 0.8840 0.0216
-4.000 0.0164 0.01397 0.00740 -0.0932 0.8777 0.0219
-3.750 0.0400 0.01308 0.00648 -0.0924 0.8733 0.0224
-3.500 0.0650 0.01245 0.00585 -0.0920 0.8693 0.0234
-3.250 0.0856 0.01206 0.00545 -0.0906 0.8623 0.0244
-3.000 0.1119 0.01165 0.00498 -0.0903 0.8573 0.0259
-2.750 0.1352 0.01120 0.00452 -0.0895 0.8514 0.0281
-2.500 0.1595 0.01088 0.00417 -0.0887 0.8445 0.0307
-2.250 0.1871 0.01047 0.00372 -0.0887 0.8394 0.0351
-2.000 0.2089 0.01017 0.00344 -0.0875 0.8310 0.0463
-1.750 0.2170 0.00820 0.00287 -0.0845 0.8241 0.4789
-1.500 0.2362 0.00790 0.00287 -0.0828 0.8154 0.5711
-1.250 0.2636 0.00778 0.00277 -0.0826 0.8088 0.6109
-1.000 0.2866 0.00769 0.00277 -0.0816 0.7999 0.6399
-0.500 0.3368 0.00758 0.00272 -0.0803 0.7832 0.6975
-0.250 0.3637 0.00754 0.00267 -0.0801 0.7749 0.7131
0.000 0.3894 0.00751 0.00263 -0.0797 0.7652 0.7234
0.250 0.4156 0.00750 0.00260 -0.0794 0.7556 0.7353
0.500 0.4422 0.00749 0.00256 -0.0791 0.7461 0.7484
0.750 0.4670 0.00748 0.00257 -0.0785 0.7352 0.7623
1.000 0.4925 0.00749 0.00257 -0.0781 0.7249 0.7773
1.250 0.5179 0.00751 0.00258 -0.0776 0.7142 0.7936
1.500 0.5422 0.00752 0.00263 -0.0768 0.7028 0.8115
1.750 0.5666 0.00756 0.00268 -0.0761 0.6916 0.8311
2.000 0.5909 0.00762 0.00273 -0.0754 0.6804 0.8517
2.250 0.6145 0.00768 0.00281 -0.0745 0.6682 0.8728
2.500 0.6385 0.00775 0.00291 -0.0736 0.6562 0.8933
2.750 0.6632 0.00787 0.00302 -0.0730 0.6442 0.9134
3.000 0.6895 0.00802 0.00314 -0.0726 0.6320 0.9320
3.250 0.7183 0.00819 0.00328 -0.0729 0.6189 0.9477
3.500 0.7495 0.00837 0.00343 -0.0738 0.6054 0.9605
3.750 0.7814 0.00856 0.00358 -0.0749 0.5917 0.9717
4.000 0.8179 0.00878 0.00374 -0.0771 0.5772 0.9788
4.250 0.8541 0.00901 0.00392 -0.0793 0.5624 0.9852
4.500 0.8919 0.00925 0.00409 -0.0819 0.5471 0.9904
4.750 0.9290 0.00949 0.00428 -0.0843 0.5312 0.9955
5.000 0.9674 0.00975 0.00449 -0.0871 0.5147 0.9999
5.250 0.9762 0.00991 0.00459 -0.0835 0.5019 1.0000
5.500 0.9848 0.01007 0.00470 -0.0798 0.4889 1.0000
5.750 0.9945 0.01023 0.00483 -0.0763 0.4761 1.0000
6.000 1.0028 0.01040 0.00496 -0.0725 0.4636 1.0000
6.250 1.0140 0.01062 0.00513 -0.0693 0.4507 1.0000
6.500 1.0278 0.01088 0.00533 -0.0668 0.4374 1.0000
6.750 1.0432 0.01116 0.00558 -0.0646 0.4237 1.0000
7.000 1.0606 0.01144 0.00583 -0.0629 0.4101 1.0000
7.250 1.0781 0.01175 0.00611 -0.0612 0.3965 1.0000
7.500 1.0958 0.01209 0.00642 -0.0597 0.3828 1.0000
7.750 1.1133 0.01245 0.00675 -0.0581 0.3690 1.0000
8.000 1.1304 0.01284 0.00710 -0.0565 0.3550 1.0000
8.250 1.1475 0.01326 0.00748 -0.0550 0.3406 1.0000
8.500 1.1643 0.01371 0.00789 -0.0534 0.3254 1.0000
8.750 1.1807 0.01419 0.00833 -0.0519 0.3096 1.0000
9.000 1.1970 0.01469 0.00879 -0.0503 0.2933 1.0000
9.250 1.2126 0.01524 0.00930 -0.0488 0.2771 1.0000
9.500 1.2279 0.01582 0.00983 -0.0472 0.2610 1.0000
9.750 1.2427 0.01645 0.01041 -0.0456 0.2447 1.0000
10.000 1.2567 0.01713 0.01104 -0.0439 0.2281 1.0000
10.250 1.2701 0.01786 0.01173 -0.0422 0.2116 1.0000
10.500 1.2826 0.01866 0.01246 -0.0404 0.1954 1.0000
10.750 1.2944 0.01951 0.01326 -0.0386 0.1794 1.0000
11.000 1.3054 0.02044 0.01413 -0.0368 0.1639 1.0000
11.250 1.3157 0.02143 0.01507 -0.0350 0.1488 1.0000
11.500 1.3258 0.02245 0.01605 -0.0332 0.1343 1.0000
11.750 1.3350 0.02355 0.01711 -0.0314 0.1206 1.0000
12.000 1.3434 0.02474 0.01825 -0.0296 0.1077 1.0000
12.250 1.3509 0.02601 0.01950 -0.0278 0.0954 1.0000
12.500 1.3573 0.02740 0.02085 -0.0259 0.0841 1.0000
12.750 1.3627 0.02890 0.02232 -0.0241 0.0740 1.0000
13.000 1.3671 0.03053 0.02393 -0.0224 0.0650 1.0000
13.250 1.3724 0.03215 0.02556 -0.0209 0.0577 1.0000
13.500 1.3770 0.03387 0.02731 -0.0194 0.0517 1.0000
13.750 1.3790 0.03589 0.02934 -0.0179 0.0468 1.0000
14.000 1.3831 0.03779 0.03129 -0.0166 0.0429 1.0000
14.250 1.3837 0.04008 0.03362 -0.0154 0.0397 1.0000
14.500 1.3876 0.04212 0.03573 -0.0144 0.0371 1.0000
14.750 1.3857 0.04479 0.03844 -0.0134 0.0349 1.0000
15.000 1.3869 0.04726 0.04100 -0.0126 0.0331 1.0000
15.250 1.3889 0.04971 0.04355 -0.0121 0.0316 1.0000
15.500 1.3873 0.05261 0.04651 -0.0116 0.0303 1.0000
15.750 1.3796 0.05625 0.05022 -0.0111 0.0291 1.0000
16.000 1.3789 0.05923 0.05331 -0.0109 0.0282 1.0000
16.250 1.3786 0.06222 0.05640 -0.0109 0.0272 1.0000
16.500 1.3767 0.06544 0.05972 -0.0109 0.0263 1.0000
16.750 1.3726 0.06899 0.06334 -0.0112 0.0255 1.0000
17.000 1.3647 0.07308 0.06751 -0.0115 0.0248 1.0000
17.250 1.3525 0.07779 0.07230 -0.0120 0.0242 1.0000
17.500 1.3509 0.08123 0.07586 -0.0126 0.0237 1.0000
17.750 1.3474 0.08494 0.07969 -0.0132 0.0232 1.0000
18.000 1.3431 0.08882 0.08367 -0.0140 0.0227 1.0000
18.250 1.3384 0.09279 0.08774 -0.0149 0.0222 1.0000
18.500 1.3333 0.09686 0.09189 -0.0159 0.0217 1.0000
18.750 1.3278 0.10100 0.09611 -0.0171 0.0213 1.0000
19.000 1.3215 0.10524 0.10042 -0.0183 0.0209 1.0000
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Polar data table (+)
Polar graphs
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