RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: RAE 2822 AIRFOIL (rae2822-il) Reynolds number: 500,000 Max Cl/Cd: 70.64 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae2822-il-500000.txt Download as CSV file: xf-rae2822-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6745 0.09877 0.09631 -0.0380 1.0000 0.0153
-13.500 -0.7207 0.08290 0.08032 -0.0480 1.0000 0.0142
-13.250 -0.7656 0.07097 0.06819 -0.0555 1.0000 0.0139
-13.000 -0.7981 0.06297 0.05999 -0.0597 1.0000 0.0136
-12.750 -0.8409 0.05445 0.05115 -0.0630 1.0000 0.0133
-12.500 -0.8719 0.04828 0.04468 -0.0641 1.0000 0.0131
-12.250 -0.8853 0.04472 0.04093 -0.0640 1.0000 0.0131
-12.000 -0.9028 0.04087 0.03683 -0.0631 1.0000 0.0131
-11.750 -0.9053 0.03908 0.03496 -0.0619 1.0000 0.0134
-11.500 -0.9109 0.03725 0.03300 -0.0599 1.0000 0.0136
-11.250 -0.9205 0.03550 0.03112 -0.0568 1.0000 0.0138
-11.000 -0.9298 0.03440 0.02992 -0.0526 1.0000 0.0140
-10.750 -0.9333 0.03281 0.02818 -0.0492 1.0000 0.0143
-10.500 -0.9348 0.03110 0.02626 -0.0458 1.0000 0.0146
-10.250 -0.9334 0.02953 0.02450 -0.0425 1.0000 0.0149
-10.000 -0.9291 0.02797 0.02275 -0.0396 1.0000 0.0151
-9.750 -0.9219 0.02678 0.02140 -0.0369 1.0000 0.0154
-9.500 -0.9127 0.02579 0.02025 -0.0344 1.0000 0.0157
-9.250 -0.9051 0.02375 0.01802 -0.0319 1.0000 0.0161
-9.000 -0.8855 0.02196 0.01614 -0.0316 0.9990 0.0168
-8.750 -0.8553 0.02092 0.01505 -0.0333 0.9968 0.0176
-8.500 -0.8234 0.02006 0.01411 -0.0351 0.9949 0.0187
-8.250 -0.7926 0.01931 0.01329 -0.0365 0.9926 0.0200
-8.000 -0.7609 0.01885 0.01273 -0.0379 0.9899 0.0210
-7.750 -0.7344 0.01705 0.01086 -0.0391 0.9870 0.0227
-7.500 -0.7014 0.01634 0.01012 -0.0410 0.9850 0.0246
-7.250 -0.6670 0.01575 0.00947 -0.0431 0.9835 0.0266
-7.000 -0.6407 0.01488 0.00854 -0.0436 0.9791 0.0290
-6.750 -0.6097 0.01420 0.00786 -0.0450 0.9759 0.0325
-6.500 -0.5758 0.01376 0.00734 -0.0468 0.9737 0.0358
-6.250 -0.5418 0.01297 0.00657 -0.0488 0.9719 0.0430
-6.000 -0.5062 0.01238 0.00599 -0.0511 0.9706 0.0526
-5.750 -0.4801 0.01187 0.00551 -0.0512 0.9655 0.0667
-5.500 -0.4484 0.01127 0.00504 -0.0526 0.9624 0.0963
-5.250 -0.4152 0.01044 0.00452 -0.0547 0.9602 0.1618
-5.000 -0.3832 0.00890 0.00373 -0.0573 0.9584 0.3318
-4.750 -0.3486 0.00817 0.00349 -0.0595 0.9570 0.4668
-4.500 -0.3185 0.00807 0.00341 -0.0601 0.9530 0.4989
-4.250 -0.2872 0.00801 0.00333 -0.0608 0.9490 0.5181
-4.000 -0.2532 0.00795 0.00323 -0.0621 0.9462 0.5327
-3.750 -0.2183 0.00792 0.00315 -0.0636 0.9439 0.5455
-3.500 -0.1835 0.00787 0.00311 -0.0651 0.9418 0.5564
-3.250 -0.1577 0.00785 0.00307 -0.0646 0.9353 0.5652
-3.000 -0.1258 0.00786 0.00302 -0.0654 0.9313 0.5752
-2.750 -0.0935 0.00787 0.00307 -0.0662 0.9281 0.5872
-2.500 -0.0661 0.00787 0.00307 -0.0661 0.9222 0.5948
-2.250 -0.0363 0.00780 0.00298 -0.0665 0.9170 0.5984
-2.000 -0.0048 0.00773 0.00286 -0.0672 0.9131 0.6017
-1.750 0.0227 0.00770 0.00279 -0.0672 0.9065 0.6051
-1.500 0.0520 0.00760 0.00270 -0.0675 0.9011 0.6081
-1.250 0.0816 0.00755 0.00265 -0.0678 0.8961 0.6112
-1.000 0.1092 0.00752 0.00262 -0.0678 0.8894 0.6145
-0.750 0.1390 0.00749 0.00255 -0.0681 0.8842 0.6181
-0.500 0.1667 0.00746 0.00253 -0.0681 0.8774 0.6215
-0.250 0.1953 0.00742 0.00251 -0.0682 0.8713 0.6248
0.000 0.2236 0.00741 0.00251 -0.0683 0.8648 0.6284
0.250 0.2517 0.00739 0.00249 -0.0683 0.8571 0.6322
0.500 0.2797 0.00738 0.00246 -0.0683 0.8491 0.6359
0.750 0.3076 0.00733 0.00245 -0.0682 0.8402 0.6394
1.000 0.3345 0.00731 0.00246 -0.0678 0.8292 0.6435
1.250 0.3619 0.00731 0.00244 -0.0676 0.8174 0.6478
1.500 0.3882 0.00727 0.00240 -0.0670 0.8004 0.6517
1.750 0.4138 0.00726 0.00235 -0.0663 0.7780 0.6555
2.000 0.4400 0.00729 0.00237 -0.0658 0.7592 0.6600
2.250 0.4665 0.00734 0.00240 -0.0654 0.7405 0.6649
2.500 0.4922 0.00738 0.00245 -0.0648 0.7186 0.6691
2.750 0.5173 0.00748 0.00251 -0.0641 0.6900 0.6739
3.000 0.5411 0.00766 0.00257 -0.0632 0.6481 0.6791
3.250 0.5615 0.00799 0.00269 -0.0616 0.5753 0.6836
3.500 0.5734 0.00897 0.00300 -0.0586 0.4227 0.6886
3.750 0.5871 0.01012 0.00346 -0.0564 0.2693 0.6944
4.000 0.6036 0.01110 0.00392 -0.0547 0.1488 0.6995
4.250 0.6235 0.01185 0.00434 -0.0535 0.0823 0.7055
4.500 0.6464 0.01233 0.00475 -0.0526 0.0605 0.7115
4.750 0.6694 0.01277 0.00520 -0.0518 0.0499 0.7174
5.000 0.6933 0.01318 0.00560 -0.0511 0.0431 0.7243
5.250 0.7158 0.01365 0.00616 -0.0501 0.0387 0.7306
5.500 0.7396 0.01404 0.00660 -0.0495 0.0352 0.7383
5.750 0.7581 0.01492 0.00754 -0.0478 0.0312 0.7452
6.000 0.7827 0.01521 0.00789 -0.0473 0.0295 0.7534
6.250 0.8053 0.01565 0.00842 -0.0464 0.0274 0.7609
6.500 0.8275 0.01620 0.00901 -0.0455 0.0257 0.7698
6.750 0.8439 0.01762 0.01054 -0.0436 0.0237 0.7784
7.000 0.8676 0.01794 0.01097 -0.0429 0.0227 0.7881
7.250 0.8903 0.01849 0.01160 -0.0421 0.0214 0.7989
7.500 0.9120 0.01911 0.01233 -0.0411 0.0204 0.8098
7.750 0.9333 0.01979 0.01310 -0.0401 0.0194 0.8215
8.000 0.9532 0.02122 0.01464 -0.0390 0.0184 0.8344
8.250 0.9744 0.02312 0.01676 -0.0380 0.0178 0.8487
8.500 0.9944 0.02397 0.01783 -0.0366 0.0173 0.8671
8.750 1.0122 0.02491 0.01901 -0.0348 0.0166 0.8913
9.000 1.0272 0.02558 0.01993 -0.0325 0.0159 0.9467
9.250 1.0503 0.02670 0.02118 -0.0323 0.0152 1.0000
9.500 1.0688 0.02812 0.02275 -0.0313 0.0148 1.0000
9.750 1.0858 0.02937 0.02410 -0.0302 0.0144 1.0000
10.000 1.0997 0.03136 0.02624 -0.0287 0.0140 1.0000
10.250 1.1057 0.03472 0.02990 -0.0264 0.0137 1.0000
10.500 1.1015 0.03891 0.03449 -0.0230 0.0136 1.0000
10.750 1.0888 0.04285 0.03879 -0.0186 0.0135 1.0000
11.000 1.0792 0.04545 0.04162 -0.0146 0.0135 1.0000
11.250 1.0652 0.04842 0.04482 -0.0108 0.0136 1.0000
11.500 1.0526 0.05126 0.04785 -0.0079 0.0136 1.0000
11.750 1.0257 0.05582 0.05267 -0.0053 0.0136 1.0000
12.000 1.0166 0.05864 0.05563 -0.0043 0.0136 1.0000
12.250 0.9917 0.06372 0.06092 -0.0042 0.0136 1.0000
12.500 0.9760 0.06819 0.06557 -0.0052 0.0138 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RAE 2822 AIRFOIL (rae2822-il)