RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.8 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32-il-1000000-n5.txt Download as CSV file: xf-raf32-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7122 0.06428 0.06162 -0.0995 0.9910 0.0080
-14.500 -0.7959 0.04412 0.04114 -0.1186 0.9847 0.0077
-14.250 -0.8236 0.03026 0.02693 -0.1374 0.9761 0.0077
-13.750 -0.7916 0.02371 0.01998 -0.1491 0.9642 0.0080
-13.500 -0.7720 0.02200 0.01814 -0.1510 0.9584 0.0082
-13.250 -0.7458 0.02064 0.01666 -0.1532 0.9546 0.0084
-13.000 -0.7253 0.01963 0.01554 -0.1536 0.9473 0.0087
-12.750 -0.7005 0.01867 0.01448 -0.1545 0.9412 0.0089
-12.500 -0.6776 0.01789 0.01359 -0.1548 0.9323 0.0092
-12.250 -0.6552 0.01718 0.01277 -0.1547 0.9228 0.0095
-12.000 -0.6320 0.01655 0.01201 -0.1547 0.9142 0.0098
-11.750 -0.6097 0.01600 0.01136 -0.1543 0.9058 0.0100
-11.500 -0.5881 0.01533 0.01059 -0.1539 0.8985 0.0105
-11.250 -0.5659 0.01478 0.00996 -0.1534 0.8907 0.0110
-11.000 -0.5426 0.01430 0.00940 -0.1530 0.8838 0.0115
-10.750 -0.5193 0.01386 0.00888 -0.1526 0.8767 0.0120
-10.500 -0.4952 0.01347 0.00838 -0.1522 0.8702 0.0125
-10.250 -0.4717 0.01300 0.00785 -0.1518 0.8640 0.0131
-10.000 -0.4479 0.01259 0.00737 -0.1513 0.8574 0.0139
-9.750 -0.4233 0.01224 0.00694 -0.1510 0.8516 0.0147
-9.500 -0.3983 0.01192 0.00656 -0.1506 0.8460 0.0155
-9.250 -0.3738 0.01154 0.00612 -0.1503 0.8405 0.0168
-9.000 -0.3487 0.01123 0.00574 -0.1499 0.8356 0.0183
-8.750 -0.3231 0.01094 0.00541 -0.1497 0.8305 0.0196
-8.500 -0.2980 0.01062 0.00505 -0.1493 0.8250 0.0219
-8.250 -0.2723 0.01038 0.00475 -0.1490 0.8199 0.0239
-8.000 -0.2464 0.01009 0.00446 -0.1488 0.8153 0.0277
-7.750 -0.2203 0.00986 0.00423 -0.1486 0.8105 0.0317
-7.500 -0.1940 0.00969 0.00405 -0.1484 0.8059 0.0361
-7.250 -0.1673 0.00953 0.00385 -0.1482 0.8017 0.0388
-7.000 -0.1404 0.00938 0.00371 -0.1481 0.7969 0.0422
-6.750 -0.1136 0.00927 0.00356 -0.1479 0.7917 0.0446
-6.500 -0.0867 0.00918 0.00342 -0.1477 0.7870 0.0462
-6.250 -0.0593 0.00909 0.00329 -0.1476 0.7823 0.0471
-6.000 -0.0326 0.00893 0.00310 -0.1475 0.7774 0.0487
-5.500 0.0211 0.00866 0.00277 -0.1471 0.7678 0.0528
-5.250 0.0481 0.00856 0.00265 -0.1469 0.7621 0.0546
-5.000 0.0747 0.00849 0.00252 -0.1467 0.7565 0.0561
-4.750 0.1021 0.00839 0.00240 -0.1466 0.7512 0.0571
-4.500 0.1291 0.00831 0.00227 -0.1464 0.7454 0.0577
-4.250 0.1558 0.00823 0.00215 -0.1461 0.7397 0.0585
-4.000 0.1827 0.00811 0.00200 -0.1459 0.7334 0.0606
-3.750 0.2091 0.00802 0.00188 -0.1456 0.7266 0.0628
-3.500 0.2361 0.00794 0.00178 -0.1455 0.7205 0.0649
-3.250 0.2627 0.00788 0.00170 -0.1452 0.7128 0.0672
-3.000 0.2892 0.00784 0.00162 -0.1449 0.7047 0.0694
-2.750 0.3150 0.00780 0.00154 -0.1444 0.6949 0.0748
-2.500 0.3412 0.00774 0.00148 -0.1441 0.6856 0.0819
-2.250 0.3668 0.00766 0.00142 -0.1436 0.6773 0.0982
-2.000 0.3931 0.00752 0.00136 -0.1434 0.6703 0.1276
-1.750 0.4187 0.00742 0.00132 -0.1430 0.6636 0.1590
-1.500 0.4451 0.00733 0.00130 -0.1427 0.6576 0.1860
-1.250 0.4715 0.00729 0.00129 -0.1425 0.6514 0.2087
-1.000 0.4976 0.00728 0.00129 -0.1421 0.6455 0.2260
-0.750 0.5245 0.00725 0.00130 -0.1419 0.6403 0.2426
-0.500 0.5511 0.00723 0.00131 -0.1417 0.6349 0.2580
-0.250 0.5769 0.00722 0.00134 -0.1413 0.6297 0.2803
0.000 0.6038 0.00719 0.00136 -0.1411 0.6250 0.3016
0.250 0.6302 0.00718 0.00139 -0.1408 0.6198 0.3202
0.500 0.6562 0.00719 0.00143 -0.1405 0.6150 0.3368
0.750 0.6827 0.00716 0.00147 -0.1402 0.6107 0.3636
1.000 0.7088 0.00710 0.00152 -0.1399 0.6058 0.4055
1.250 0.7343 0.00708 0.00158 -0.1395 0.6007 0.4425
1.500 0.7599 0.00708 0.00165 -0.1391 0.5950 0.4739
1.750 0.7856 0.00708 0.00172 -0.1387 0.5883 0.5035
2.000 0.8101 0.00712 0.00181 -0.1380 0.5812 0.5355
2.250 0.8360 0.00714 0.00188 -0.1376 0.5742 0.5615
2.500 0.8597 0.00721 0.00197 -0.1368 0.5641 0.5837
2.750 0.8837 0.00727 0.00206 -0.1360 0.5524 0.6087
3.000 0.9075 0.00734 0.00216 -0.1352 0.5409 0.6313
3.250 0.9301 0.00743 0.00227 -0.1341 0.5274 0.6562
3.500 0.9518 0.00751 0.00240 -0.1329 0.5129 0.6910
3.750 0.9729 0.00758 0.00254 -0.1316 0.4999 0.7354
4.000 0.9917 0.00764 0.00270 -0.1297 0.4832 0.7934
4.250 1.0326 0.00766 0.00297 -0.1328 0.4592 1.0000
4.500 1.0536 0.00787 0.00313 -0.1315 0.4454 1.0000
4.750 1.0725 0.00811 0.00330 -0.1298 0.4294 1.0000
5.000 1.0893 0.00842 0.00352 -0.1276 0.4094 1.0000
5.250 1.1061 0.00874 0.00374 -0.1254 0.3881 1.0000
5.500 1.1240 0.00903 0.00397 -0.1236 0.3702 1.0000
5.750 1.1411 0.00937 0.00422 -0.1215 0.3493 1.0000
6.000 1.1541 0.00986 0.00456 -0.1188 0.3169 1.0000
6.250 1.1639 0.01051 0.00500 -0.1156 0.2771 1.0000
6.500 1.1702 0.01131 0.00555 -0.1118 0.2323 1.0000
6.750 1.1811 0.01195 0.00604 -0.1089 0.2031 1.0000
7.000 1.1918 0.01261 0.00654 -0.1060 0.1732 1.0000
7.250 1.2046 0.01320 0.00702 -0.1036 0.1490 1.0000
7.500 1.2110 0.01410 0.00771 -0.1002 0.1125 1.0000
7.750 1.2205 0.01489 0.00837 -0.0974 0.0881 1.0000
8.000 1.2323 0.01559 0.00900 -0.0950 0.0733 1.0000
8.250 1.2472 0.01616 0.00954 -0.0932 0.0660 1.0000
8.500 1.2629 0.01670 0.01007 -0.0915 0.0608 1.0000
8.750 1.2781 0.01727 0.01064 -0.0898 0.0561 1.0000
9.000 1.2937 0.01785 0.01122 -0.0882 0.0519 1.0000
9.250 1.3094 0.01842 0.01181 -0.0866 0.0476 1.0000
9.500 1.3226 0.01916 0.01251 -0.0848 0.0408 1.0000
9.750 1.3343 0.02000 0.01331 -0.0829 0.0324 1.0000
10.000 1.3464 0.02085 0.01414 -0.0811 0.0271 1.0000
10.250 1.3591 0.02168 0.01497 -0.0794 0.0235 1.0000
10.500 1.3701 0.02263 0.01592 -0.0776 0.0202 1.0000
10.750 1.3835 0.02346 0.01678 -0.0761 0.0186 1.0000
11.000 1.3950 0.02443 0.01777 -0.0744 0.0170 1.0000
11.250 1.4070 0.02540 0.01876 -0.0729 0.0158 1.0000
11.500 1.4186 0.02641 0.01980 -0.0714 0.0145 1.0000
11.750 1.4289 0.02753 0.02095 -0.0699 0.0133 1.0000
12.000 1.4404 0.02859 0.02205 -0.0685 0.0126 1.0000
12.250 1.4512 0.02973 0.02323 -0.0671 0.0120 1.0000
12.500 1.4613 0.03094 0.02447 -0.0657 0.0113 1.0000
12.750 1.4704 0.03227 0.02584 -0.0643 0.0106 1.0000
13.000 1.4797 0.03361 0.02723 -0.0630 0.0103 1.0000
13.250 1.4893 0.03495 0.02862 -0.0618 0.0099 1.0000
13.500 1.4981 0.03638 0.03010 -0.0606 0.0095 1.0000
13.750 1.5059 0.03793 0.03171 -0.0595 0.0091 1.0000
14.000 1.5131 0.03958 0.03339 -0.0583 0.0086 1.0000
14.250 1.5191 0.04137 0.03524 -0.0572 0.0083 1.0000
14.500 1.5268 0.04303 0.03696 -0.0562 0.0080 1.0000
14.750 1.5335 0.04482 0.03881 -0.0553 0.0077 1.0000
15.000 1.5395 0.04673 0.04079 -0.0545 0.0075 1.0000
15.250 1.5448 0.04874 0.04287 -0.0536 0.0072 1.0000
15.500 1.5500 0.05081 0.04499 -0.0529 0.0071 1.0000
15.750 1.5535 0.05307 0.04731 -0.0522 0.0068 1.0000
16.000 1.5558 0.05551 0.04981 -0.0515 0.0066 1.0000
16.250 1.5580 0.05801 0.05239 -0.0510 0.0065 1.0000
16.500 1.5614 0.06044 0.05489 -0.0505 0.0063 1.0000
16.750 1.5639 0.06300 0.05753 -0.0502 0.0062 1.0000
17.000 1.5659 0.06565 0.06026 -0.0499 0.0061 1.0000
17.250 1.5672 0.06842 0.06311 -0.0497 0.0060 1.0000
17.500 1.5671 0.07145 0.06622 -0.0496 0.0058 1.0000
17.750 1.5675 0.07446 0.06931 -0.0497 0.0056 1.0000
18.000 1.5671 0.07762 0.07255 -0.0498 0.0055 1.0000
18.250 1.5658 0.08096 0.07598 -0.0501 0.0054 1.0000
18.500 1.5632 0.08451 0.07961 -0.0505 0.0053 1.0000
18.750 1.5598 0.08829 0.08348 -0.0511 0.0052 1.0000
19.000 1.5552 0.09231 0.08759 -0.0519 0.0051 1.0000
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Polar data table (+)
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