RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 100,000 Max Cl/Cd: 53.74 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg8-il-100000-n5.txt Download as CSV file: xf-rg8-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 8 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4916 0.09194 0.08677 -0.0401 1.0000 0.0281
-10.000 -0.4999 0.08636 0.08126 -0.0422 1.0000 0.0279
-9.750 -0.5114 0.08002 0.07499 -0.0450 1.0000 0.0276
-9.500 -0.5307 0.07161 0.06662 -0.0499 1.0000 0.0271
-9.250 -0.5575 0.06467 0.05969 -0.0541 1.0000 0.0268
-9.000 -0.5855 0.06041 0.05541 -0.0548 1.0000 0.0265
-8.750 -0.6080 0.05592 0.05079 -0.0551 1.0000 0.0263
-8.500 -0.6228 0.05171 0.04636 -0.0546 1.0000 0.0262
-8.250 -0.6313 0.04753 0.04188 -0.0538 1.0000 0.0262
-8.000 -0.6333 0.04354 0.03751 -0.0528 1.0000 0.0263
-7.750 -0.6293 0.03985 0.03338 -0.0519 1.0000 0.0265
-7.500 -0.6199 0.03664 0.02973 -0.0510 1.0000 0.0268
-7.250 -0.6064 0.03398 0.02660 -0.0501 1.0000 0.0278
-7.000 -0.5898 0.03191 0.02405 -0.0492 1.0000 0.0290
-6.750 -0.5729 0.02969 0.02167 -0.0485 1.0000 0.0301
-6.500 -0.5539 0.02799 0.01977 -0.0476 1.0000 0.0309
-6.250 -0.5338 0.02648 0.01807 -0.0468 1.0000 0.0318
-6.000 -0.5131 0.02515 0.01655 -0.0459 1.0000 0.0329
-5.750 -0.4919 0.02395 0.01519 -0.0451 1.0000 0.0342
-5.500 -0.4702 0.02287 0.01397 -0.0443 1.0000 0.0359
-5.250 -0.4483 0.02196 0.01290 -0.0435 1.0000 0.0379
-5.000 -0.4214 0.02102 0.01195 -0.0441 0.9984 0.0421
-4.750 -0.3861 0.02030 0.01107 -0.0460 0.9944 0.0490
-4.500 -0.3522 0.01936 0.01013 -0.0478 0.9900 0.0598
-4.250 -0.3172 0.01856 0.00942 -0.0498 0.9856 0.0860
-4.000 -0.2826 0.01794 0.00899 -0.0518 0.9810 0.1306
-3.750 -0.2496 0.01722 0.00864 -0.0538 0.9755 0.2011
-3.500 -0.2135 0.01659 0.00827 -0.0561 0.9711 0.2753
-3.250 -0.1829 0.01595 0.00800 -0.0572 0.9645 0.3654
-3.000 -0.1489 0.01558 0.00806 -0.0586 0.9591 0.4781
-2.750 -0.1185 0.01549 0.00805 -0.0590 0.9515 0.5451
-2.500 -0.0829 0.01546 0.00799 -0.0603 0.9457 0.5884
-2.250 -0.0530 0.01542 0.00791 -0.0606 0.9373 0.6197
-2.000 -0.0169 0.01537 0.00783 -0.0619 0.9316 0.6474
-1.750 0.0123 0.01531 0.00772 -0.0619 0.9225 0.6702
-1.500 0.0489 0.01521 0.00760 -0.0633 0.9170 0.6919
-1.000 0.1112 0.01500 0.00734 -0.0639 0.9003 0.7289
-0.750 0.1424 0.01487 0.00721 -0.0641 0.8916 0.7460
-0.500 0.1735 0.01473 0.00706 -0.0644 0.8825 0.7620
-0.250 0.2095 0.01455 0.00688 -0.0656 0.8752 0.7771
0.000 0.2393 0.01443 0.00675 -0.0656 0.8642 0.7912
0.250 0.2711 0.01427 0.00660 -0.0660 0.8537 0.8044
0.500 0.3057 0.01408 0.00641 -0.0669 0.8439 0.8170
0.750 0.3379 0.01392 0.00625 -0.0674 0.8321 0.8299
1.000 0.3686 0.01378 0.00613 -0.0676 0.8187 0.8433
1.250 0.3993 0.01364 0.00601 -0.0677 0.8047 0.8576
1.500 0.4302 0.01351 0.00589 -0.0679 0.7898 0.8730
1.750 0.4616 0.01338 0.00578 -0.0681 0.7740 0.8908
2.000 0.4929 0.01329 0.00572 -0.0684 0.7561 0.9124
2.250 0.5289 0.01322 0.00566 -0.0698 0.7369 0.9380
2.500 0.5707 0.01318 0.00561 -0.0724 0.7165 0.9740
2.750 0.6026 0.01325 0.00563 -0.0733 0.6943 1.0000
3.250 0.6601 0.01356 0.00579 -0.0737 0.6488 1.0000
3.500 0.6875 0.01376 0.00594 -0.0735 0.6248 1.0000
3.750 0.7143 0.01399 0.00609 -0.0732 0.6003 1.0000
4.000 0.7398 0.01425 0.00629 -0.0728 0.5747 1.0000
4.250 0.7650 0.01454 0.00651 -0.0722 0.5487 1.0000
4.500 0.7896 0.01486 0.00679 -0.0715 0.5224 1.0000
4.750 0.8136 0.01521 0.00707 -0.0708 0.4956 1.0000
5.000 0.8370 0.01559 0.00738 -0.0699 0.4685 1.0000
5.250 0.8599 0.01600 0.00772 -0.0690 0.4408 1.0000
5.500 0.8823 0.01644 0.00813 -0.0680 0.4127 1.0000
5.750 0.9041 0.01691 0.00855 -0.0670 0.3842 1.0000
6.000 0.9255 0.01742 0.00900 -0.0659 0.3556 1.0000
6.250 0.9465 0.01796 0.00949 -0.0648 0.3270 1.0000
6.500 0.9669 0.01855 0.01002 -0.0636 0.2983 1.0000
6.750 0.9867 0.01918 0.01062 -0.0624 0.2696 1.0000
7.000 1.0060 0.01986 0.01125 -0.0611 0.2410 1.0000
7.250 1.0249 0.02060 0.01193 -0.0598 0.2135 1.0000
7.500 1.0432 0.02138 0.01267 -0.0585 0.1869 1.0000
7.750 1.0609 0.02223 0.01348 -0.0571 0.1624 1.0000
8.000 1.0775 0.02317 0.01436 -0.0556 0.1404 1.0000
8.250 1.0941 0.02412 0.01536 -0.0540 0.1205 1.0000
8.500 1.1086 0.02521 0.01640 -0.0523 0.1024 1.0000
8.750 1.1229 0.02632 0.01749 -0.0506 0.0844 1.0000
9.000 1.1360 0.02748 0.01860 -0.0488 0.0671 1.0000
9.250 1.1469 0.02871 0.01981 -0.0467 0.0538 1.0000
9.500 1.1563 0.03003 0.02117 -0.0444 0.0441 1.0000
9.750 1.1633 0.03153 0.02272 -0.0418 0.0369 1.0000
10.000 1.1683 0.03317 0.02444 -0.0392 0.0323 1.0000
10.250 1.1709 0.03503 0.02646 -0.0364 0.0292 1.0000
10.500 1.1749 0.03686 0.02847 -0.0339 0.0268 1.0000
10.750 1.1781 0.03874 0.03047 -0.0318 0.0247 1.0000
11.000 1.1784 0.04092 0.03274 -0.0297 0.0232 1.0000
11.250 1.1801 0.04319 0.03516 -0.0279 0.0219 1.0000
11.500 1.1833 0.04542 0.03761 -0.0265 0.0204 1.0000
11.750 1.1848 0.04787 0.04024 -0.0252 0.0195 1.0000
12.000 1.1849 0.05054 0.04308 -0.0242 0.0187 1.0000
12.250 1.1839 0.05344 0.04615 -0.0235 0.0181 1.0000
12.500 1.1818 0.05659 0.04945 -0.0231 0.0177 1.0000
12.750 1.1786 0.06000 0.05302 -0.0230 0.0173 1.0000
13.000 1.1740 0.06377 0.05694 -0.0233 0.0170 1.0000
13.250 1.1682 0.06790 0.06124 -0.0238 0.0168 1.0000
13.500 1.1605 0.07250 0.06606 -0.0249 0.0166 1.0000
13.750 1.1511 0.07752 0.07133 -0.0265 0.0165 1.0000
14.000 1.1390 0.08321 0.07726 -0.0288 0.0164 1.0000
14.250 1.1257 0.08936 0.08365 -0.0318 0.0164 1.0000
14.500 1.1109 0.09613 0.09064 -0.0354 0.0164 1.0000
14.750 1.0949 0.10357 0.09829 -0.0397 0.0164 1.0000
15.000 1.0778 0.11169 0.10661 -0.0447 0.0164 1.0000
15.250 1.0602 0.12046 0.11554 -0.0503 0.0165 1.0000
15.500 1.0425 0.12975 0.12498 -0.0563 0.0166 1.0000
15.750 0.9708 0.15862 0.15422 -0.0742 0.0182 1.0000
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