RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 100,000 Max Cl/Cd: 35.95 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5213-il-100000-n5.txt Download as CSV file: xf-rae5213-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5392 0.08990 0.08433 -0.0285 1.0000 0.0311
-9.750 -0.5412 0.08497 0.07944 -0.0310 1.0000 0.0309
-9.500 -0.5474 0.07872 0.07322 -0.0350 1.0000 0.0305
-9.250 -0.5604 0.07194 0.06644 -0.0401 1.0000 0.0300
-9.000 -0.5817 0.06584 0.06030 -0.0442 1.0000 0.0296
-8.750 -0.6014 0.06107 0.05542 -0.0462 1.0000 0.0293
-8.500 -0.6141 0.05632 0.05047 -0.0472 1.0000 0.0290
-8.250 -0.6210 0.05182 0.04571 -0.0474 1.0000 0.0288
-8.000 -0.6222 0.04770 0.04127 -0.0470 1.0000 0.0287
-7.750 -0.6188 0.04391 0.03713 -0.0462 1.0000 0.0289
-7.500 -0.6108 0.04069 0.03356 -0.0453 1.0000 0.0295
-7.250 -0.6007 0.03742 0.02980 -0.0443 1.0000 0.0305
-7.000 -0.5876 0.03453 0.02644 -0.0431 1.0000 0.0315
-6.750 -0.5704 0.03286 0.02464 -0.0422 1.0000 0.0323
-6.500 -0.5529 0.03086 0.02238 -0.0410 1.0000 0.0329
-6.250 -0.5343 0.02894 0.02018 -0.0398 1.0000 0.0337
-6.000 -0.5149 0.02715 0.01806 -0.0386 1.0000 0.0350
-5.750 -0.4951 0.02581 0.01655 -0.0374 1.0000 0.0367
-5.500 -0.4751 0.02476 0.01546 -0.0363 1.0000 0.0384
-5.250 -0.4546 0.02354 0.01408 -0.0351 1.0000 0.0399
-5.000 -0.4340 0.02243 0.01284 -0.0338 1.0000 0.0414
-4.750 -0.4141 0.02164 0.01210 -0.0327 1.0000 0.0436
-4.500 -0.3936 0.02085 0.01124 -0.0315 1.0000 0.0462
-4.250 -0.3735 0.02003 0.01044 -0.0303 1.0000 0.0481
-4.000 -0.3446 0.01934 0.00977 -0.0309 0.9969 0.0518
-3.750 -0.3104 0.01859 0.00903 -0.0325 0.9915 0.0558
-3.500 -0.2753 0.01794 0.00837 -0.0343 0.9860 0.0607
-3.250 -0.2414 0.01734 0.00777 -0.0359 0.9799 0.0692
-3.000 -0.2054 0.01670 0.00720 -0.0378 0.9746 0.0841
-2.750 -0.1732 0.01579 0.00666 -0.0393 0.9676 0.1426
-2.500 -0.1435 0.01403 0.00652 -0.0410 0.9626 0.4776
-2.250 -0.1146 0.01415 0.00695 -0.0407 0.9543 0.5977
-2.000 -0.0813 0.01455 0.00747 -0.0407 0.9487 0.6624
-1.750 -0.0556 0.01484 0.00783 -0.0392 0.9397 0.7011
-1.500 -0.0203 0.01490 0.00785 -0.0401 0.9345 0.7197
-1.250 0.0108 0.01483 0.00768 -0.0408 0.9255 0.7279
-1.000 0.0466 0.01474 0.00755 -0.0421 0.9194 0.7340
-0.750 0.0777 0.01467 0.00743 -0.0426 0.9100 0.7412
-0.500 0.1135 0.01457 0.00729 -0.0439 0.9031 0.7477
-0.250 0.1437 0.01451 0.00722 -0.0442 0.8936 0.7540
0.000 0.1786 0.01443 0.00710 -0.0454 0.8860 0.7610
0.250 0.2077 0.01436 0.00706 -0.0453 0.8758 0.7669
0.500 0.2417 0.01425 0.00695 -0.0461 0.8669 0.7733
0.750 0.2712 0.01414 0.00685 -0.0460 0.8522 0.7801
1.000 0.3016 0.01390 0.00661 -0.0455 0.8322 0.7859
1.250 0.3296 0.01365 0.00631 -0.0444 0.8013 0.7927
1.500 0.3571 0.01345 0.00602 -0.0432 0.7656 0.7992
1.750 0.3838 0.01335 0.00586 -0.0421 0.7337 0.8062
2.000 0.4109 0.01333 0.00579 -0.0414 0.7046 0.8139
2.250 0.4362 0.01333 0.00576 -0.0403 0.6697 0.8212
2.500 0.4615 0.01339 0.00573 -0.0392 0.6239 0.8304
2.750 0.4846 0.01353 0.00566 -0.0376 0.5538 0.8390
3.000 0.5047 0.01404 0.00564 -0.0357 0.4405 0.8495
3.250 0.5217 0.01498 0.00590 -0.0338 0.3036 0.8621
3.500 0.5410 0.01586 0.00629 -0.0325 0.2151 0.8778
4.000 0.5933 0.01699 0.00714 -0.0323 0.1565 0.9328
4.250 0.6230 0.01758 0.00765 -0.0331 0.1431 1.0000
4.500 0.6486 0.01820 0.00819 -0.0330 0.1331 1.0000
4.750 0.6740 0.01882 0.00876 -0.0329 0.1251 1.0000
5.000 0.6987 0.01949 0.00937 -0.0326 0.1180 1.0000
5.250 0.7237 0.02018 0.01005 -0.0323 0.1118 1.0000
5.500 0.7485 0.02088 0.01069 -0.0320 0.1056 1.0000
5.750 0.7730 0.02168 0.01147 -0.0316 0.1002 1.0000
6.000 0.7978 0.02239 0.01219 -0.0313 0.0942 1.0000
6.250 0.8218 0.02326 0.01298 -0.0309 0.0893 1.0000
6.500 0.8466 0.02402 0.01384 -0.0306 0.0839 1.0000
6.750 0.8703 0.02487 0.01462 -0.0302 0.0797 1.0000
7.000 0.8948 0.02578 0.01569 -0.0297 0.0751 1.0000
7.250 0.9183 0.02662 0.01653 -0.0293 0.0713 1.0000
7.500 0.9418 0.02767 0.01767 -0.0288 0.0679 1.0000
7.750 0.9650 0.02872 0.01885 -0.0283 0.0644 1.0000
8.000 0.9873 0.02959 0.01969 -0.0278 0.0620 1.0000
8.250 1.0095 0.03100 0.02136 -0.0271 0.0590 1.0000
8.500 1.0311 0.03233 0.02283 -0.0264 0.0568 1.0000
8.750 1.0521 0.03347 0.02402 -0.0258 0.0552 1.0000
9.000 1.0718 0.03511 0.02585 -0.0250 0.0535 1.0000
9.250 1.0890 0.03709 0.02817 -0.0240 0.0515 1.0000
9.500 1.1061 0.03862 0.02988 -0.0230 0.0499 1.0000
9.750 1.1233 0.03997 0.03133 -0.0221 0.0487 1.0000
10.000 1.1391 0.04168 0.03313 -0.0212 0.0479 1.0000
10.250 1.1438 0.04507 0.03707 -0.0193 0.0470 1.0000
10.500 1.1448 0.04848 0.04092 -0.0174 0.0462 1.0000
10.750 1.1412 0.05193 0.04475 -0.0153 0.0456 1.0000
11.000 1.1319 0.05533 0.04847 -0.0130 0.0451 1.0000
11.250 1.1166 0.05877 0.05219 -0.0106 0.0447 1.0000
11.500 1.0952 0.06294 0.05662 -0.0092 0.0445 1.0000
11.750 1.0651 0.06858 0.06254 -0.0097 0.0445 1.0000
12.000 1.0142 0.07841 0.07268 -0.0146 0.0449 1.0000
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Polar data table (+)
Polar graphs
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