RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 2822 AIRFOIL (rae2822-il) Reynolds number: 500,000 Max Cl/Cd: 57.37 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae2822-il-500000-n5.txt Download as CSV file: xf-rae2822-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 2822 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8266 0.10734 0.10466 -0.0317 1.0000 0.0073
-16.000 -0.8933 0.08778 0.08477 -0.0425 1.0000 0.0070
-15.750 -0.9161 0.07916 0.07598 -0.0475 1.0000 0.0070
-15.500 -0.9344 0.07214 0.06880 -0.0514 1.0000 0.0070
-15.250 -0.9503 0.06604 0.06254 -0.0545 1.0000 0.0071
-15.000 -0.9629 0.06090 0.05724 -0.0569 1.0000 0.0071
-14.750 -0.9745 0.05628 0.05247 -0.0587 1.0000 0.0071
-14.500 -0.9796 0.05279 0.04885 -0.0599 1.0000 0.0072
-14.250 -0.9884 0.04896 0.04486 -0.0608 1.0000 0.0073
-14.000 -0.9900 0.04616 0.04194 -0.0614 1.0000 0.0074
-13.750 -0.9915 0.04344 0.03909 -0.0617 1.0000 0.0077
-13.500 -0.9944 0.04067 0.03617 -0.0617 1.0000 0.0076
-13.250 -0.9941 0.03833 0.03367 -0.0615 1.0000 0.0079
-13.000 -0.9916 0.03630 0.03152 -0.0611 1.0000 0.0081
-12.750 -0.9897 0.03429 0.02936 -0.0604 1.0000 0.0082
-12.500 -0.9858 0.03256 0.02750 -0.0596 1.0000 0.0084
-12.250 -0.9812 0.03098 0.02579 -0.0585 1.0000 0.0085
-12.000 -0.9766 0.02952 0.02421 -0.0572 1.0000 0.0086
-11.750 -0.9768 0.02781 0.02242 -0.0554 1.0000 0.0088
-11.500 -0.9764 0.02645 0.02098 -0.0531 1.0000 0.0090
-11.250 -0.9777 0.02534 0.01982 -0.0502 1.0000 0.0092
-11.000 -0.9845 0.02448 0.01889 -0.0460 1.0000 0.0093
-10.750 -0.9826 0.02364 0.01799 -0.0427 1.0000 0.0095
-10.500 -0.9722 0.02280 0.01708 -0.0410 0.9995 0.0097
-10.250 -0.9448 0.02187 0.01606 -0.0424 0.9973 0.0102
-10.000 -0.9178 0.02090 0.01499 -0.0438 0.9947 0.0106
-9.750 -0.8919 0.02002 0.01401 -0.0447 0.9920 0.0111
-9.500 -0.8653 0.01922 0.01311 -0.0457 0.9889 0.0116
-9.250 -0.8382 0.01828 0.01210 -0.0469 0.9861 0.0123
-9.000 -0.8087 0.01756 0.01134 -0.0483 0.9841 0.0131
-8.750 -0.7815 0.01696 0.01068 -0.0491 0.9810 0.0140
-8.500 -0.7548 0.01635 0.01002 -0.0497 0.9773 0.0149
-8.250 -0.7256 0.01577 0.00936 -0.0508 0.9745 0.0157
-8.000 -0.6960 0.01503 0.00858 -0.0521 0.9723 0.0170
-7.750 -0.6643 0.01450 0.00801 -0.0536 0.9707 0.0186
-7.500 -0.6378 0.01406 0.00753 -0.0539 0.9665 0.0202
-7.250 -0.6093 0.01355 0.00698 -0.0547 0.9628 0.0221
-7.000 -0.5786 0.01307 0.00648 -0.0559 0.9601 0.0246
-6.750 -0.5468 0.01267 0.00603 -0.0572 0.9578 0.0273
-6.500 -0.5167 0.01222 0.00559 -0.0583 0.9547 0.0321
-6.250 -0.4899 0.01189 0.00524 -0.0584 0.9494 0.0365
-6.000 -0.4600 0.01149 0.00486 -0.0593 0.9456 0.0439
-5.750 -0.4285 0.01110 0.00449 -0.0606 0.9426 0.0548
-5.500 -0.4014 0.01076 0.00418 -0.0608 0.9372 0.0681
-5.250 -0.3731 0.01037 0.00386 -0.0613 0.9321 0.0880
-5.000 -0.3433 0.00992 0.00352 -0.0622 0.9281 0.1191
-4.750 -0.3172 0.00943 0.00320 -0.0624 0.9220 0.1638
-4.500 -0.2908 0.00873 0.00279 -0.0629 0.9162 0.2416
-4.250 -0.2661 0.00767 0.00230 -0.0633 0.9108 0.3886
-4.000 -0.2394 0.00736 0.00218 -0.0634 0.9044 0.4527
-3.750 -0.2102 0.00724 0.00210 -0.0638 0.8992 0.4821
-3.500 -0.1818 0.00718 0.00203 -0.0639 0.8934 0.5007
-3.250 -0.1532 0.00714 0.00197 -0.0641 0.8875 0.5148
-3.000 -0.1241 0.00711 0.00192 -0.0644 0.8822 0.5281
-2.750 -0.0962 0.00710 0.00192 -0.0644 0.8756 0.5440
-2.500 -0.0675 0.00708 0.00189 -0.0646 0.8699 0.5532
-2.250 -0.0390 0.00706 0.00183 -0.0648 0.8639 0.5565
-2.000 -0.0104 0.00705 0.00177 -0.0649 0.8575 0.5598
-1.750 0.0183 0.00702 0.00172 -0.0651 0.8519 0.5626
-1.500 0.0464 0.00700 0.00169 -0.0652 0.8453 0.5653
-1.250 0.0751 0.00699 0.00165 -0.0654 0.8394 0.5682
-1.000 0.1033 0.00698 0.00163 -0.0655 0.8330 0.5715
-0.750 0.1318 0.00699 0.00161 -0.0656 0.8266 0.5749
-0.500 0.1600 0.00698 0.00161 -0.0657 0.8204 0.5777
-0.250 0.1881 0.00697 0.00161 -0.0658 0.8135 0.5807
0.000 0.2164 0.00698 0.00162 -0.0659 0.8069 0.5839
0.250 0.2443 0.00699 0.00163 -0.0659 0.7984 0.5874
0.500 0.2722 0.00702 0.00164 -0.0658 0.7889 0.5908
0.750 0.2997 0.00703 0.00167 -0.0657 0.7779 0.5941
1.000 0.3269 0.00706 0.00169 -0.0655 0.7642 0.5976
1.250 0.3538 0.00711 0.00171 -0.0653 0.7477 0.6012
1.500 0.3796 0.00720 0.00173 -0.0647 0.7221 0.6047
1.750 0.4034 0.00735 0.00175 -0.0637 0.6781 0.6082
2.000 0.4271 0.00755 0.00181 -0.0628 0.6333 0.6121
2.250 0.4498 0.00784 0.00190 -0.0618 0.5754 0.6164
2.750 0.4863 0.00920 0.00240 -0.0584 0.3625 0.6239
3.000 0.5058 0.00992 0.00271 -0.0571 0.2605 0.6280
3.250 0.5272 0.01053 0.00300 -0.0562 0.1833 0.6324
3.500 0.5496 0.01105 0.00330 -0.0554 0.1239 0.6368
3.750 0.5729 0.01148 0.00358 -0.0547 0.0858 0.6415
4.000 0.5972 0.01183 0.00385 -0.0542 0.0641 0.6465
4.250 0.6220 0.01213 0.00412 -0.0537 0.0510 0.6512
4.500 0.6469 0.01241 0.00441 -0.0533 0.0429 0.6560
4.750 0.6719 0.01268 0.00470 -0.0528 0.0375 0.6613
5.000 0.6964 0.01300 0.00502 -0.0523 0.0323 0.6667
5.250 0.7211 0.01328 0.00536 -0.0518 0.0293 0.6725
5.500 0.7456 0.01359 0.00571 -0.0513 0.0266 0.6786
5.750 0.7688 0.01401 0.00616 -0.0505 0.0238 0.6843
6.000 0.7932 0.01431 0.00653 -0.0500 0.0222 0.6905
6.250 0.8173 0.01464 0.00690 -0.0494 0.0204 0.6966
6.500 0.8403 0.01505 0.00737 -0.0486 0.0189 0.7033
6.750 0.8625 0.01556 0.00794 -0.0477 0.0177 0.7105
7.000 0.8853 0.01597 0.00844 -0.0469 0.0168 0.7178
7.250 0.9081 0.01640 0.00894 -0.0462 0.0158 0.7253
7.500 0.9307 0.01680 0.00942 -0.0454 0.0148 0.7329
7.750 0.9519 0.01736 0.01002 -0.0444 0.0138 0.7408
8.000 0.9725 0.01797 0.01073 -0.0433 0.0132 0.7496
8.250 0.9932 0.01854 0.01142 -0.0422 0.0127 0.7587
8.500 1.0137 0.01914 0.01213 -0.0411 0.0122 0.7688
8.750 1.0338 0.01972 0.01283 -0.0400 0.0116 0.7789
9.000 1.0533 0.02035 0.01357 -0.0388 0.0112 0.7897
9.250 1.0725 0.02095 0.01428 -0.0375 0.0108 0.8021
9.500 1.0902 0.02165 0.01509 -0.0361 0.0104 0.8164
9.750 1.1045 0.02264 0.01620 -0.0341 0.0100 0.8327
10.000 1.1198 0.02333 0.01707 -0.0322 0.0097 0.8524
10.250 1.1334 0.02395 0.01790 -0.0299 0.0094 0.8795
10.500 1.1475 0.02464 0.01884 -0.0278 0.0091 0.9725
10.750 1.1616 0.02561 0.01993 -0.0260 0.0088 1.0000
11.000 1.1745 0.02668 0.02112 -0.0242 0.0085 1.0000
11.250 1.1866 0.02777 0.02234 -0.0223 0.0083 1.0000
11.500 1.1975 0.02892 0.02360 -0.0204 0.0081 1.0000
11.750 1.2086 0.02992 0.02471 -0.0186 0.0079 1.0000
12.000 1.2167 0.03125 0.02616 -0.0166 0.0078 1.0000
12.250 1.2247 0.03251 0.02752 -0.0147 0.0076 1.0000
12.500 1.2293 0.03410 0.02924 -0.0127 0.0075 1.0000
12.750 1.2308 0.03600 0.03128 -0.0107 0.0073 1.0000
13.000 1.2280 0.03839 0.03386 -0.0087 0.0072 1.0000
13.250 1.2233 0.04108 0.03675 -0.0069 0.0072 1.0000
13.500 1.2198 0.04373 0.03959 -0.0056 0.0071 1.0000
13.750 1.2128 0.04687 0.04295 -0.0046 0.0070 1.0000
14.000 1.2031 0.05050 0.04678 -0.0041 0.0070 1.0000
14.250 1.1909 0.05469 0.05119 -0.0043 0.0070 1.0000
14.500 1.1765 0.05951 0.05621 -0.0053 0.0069 1.0000
14.750 1.1570 0.06558 0.06250 -0.0076 0.0069 1.0000
15.000 1.1325 0.07330 0.07043 -0.0115 0.0069 1.0000
15.250 1.1066 0.08261 0.07995 -0.0174 0.0069 1.0000
15.500 1.0709 0.09603 0.09360 -0.0265 0.0070 1.0000
15.750 0.9840 0.12548 0.12336 -0.0442 0.0073 1.0000
16.250 0.8193 0.19052 0.18840 -0.0756 0.0069 1.0000
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Polar data table (+)
Polar graphs
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