DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 200,000 Max Cl/Cd: 52 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-doa5-il-200000.txt Download as CSV file: xf-doa5-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DORNIER A-5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5657 0.09913 0.09550 -0.0535 1.0000 0.0841
-11.000 -0.6126 0.09350 0.08985 -0.0545 1.0000 0.0842
-10.750 -0.6517 0.08973 0.08604 -0.0534 1.0000 0.0842
-10.500 -0.6914 0.08679 0.08306 -0.0510 1.0000 0.0842
-10.250 -0.7320 0.08334 0.07942 -0.0525 0.9946 0.0844
-10.000 -0.7631 0.08022 0.07593 -0.0534 0.9868 0.0847
-9.750 -0.7386 0.07224 0.06820 -0.0552 0.9869 0.0866
-9.500 -0.7132 0.06957 0.06559 -0.0567 0.9849 0.0884
-9.250 -0.7101 0.06655 0.06246 -0.0571 0.9795 0.0901
-9.000 -0.7077 0.06332 0.05904 -0.0581 0.9743 0.0930
-8.750 -0.7586 0.04780 0.04187 -0.0536 0.9647 0.0621
-8.500 -0.7409 0.04422 0.03806 -0.0540 0.9622 0.0606
-8.250 -0.7188 0.04111 0.03458 -0.0549 0.9601 0.0602
-8.000 -0.7112 0.03901 0.03222 -0.0523 0.9552 0.0600
-7.750 -0.6912 0.03672 0.02963 -0.0518 0.9520 0.0597
-7.500 -0.6645 0.03468 0.02730 -0.0523 0.9495 0.0597
-7.250 -0.6329 0.03299 0.02537 -0.0536 0.9477 0.0599
-7.000 -0.6137 0.03188 0.02408 -0.0523 0.9437 0.0609
-6.750 -0.5927 0.03097 0.02300 -0.0514 0.9398 0.0620
-6.500 -0.5648 0.03012 0.02195 -0.0517 0.9371 0.0629
-6.250 -0.5332 0.02901 0.02072 -0.0526 0.9351 0.0638
-6.000 -0.4994 0.02784 0.01962 -0.0539 0.9336 0.0654
-5.750 -0.4837 0.02722 0.01902 -0.0519 0.9276 0.0668
-5.500 -0.4557 0.02657 0.01837 -0.0522 0.9236 0.0687
-5.250 -0.4212 0.02602 0.01776 -0.0536 0.9208 0.0719
-5.000 -0.3864 0.02520 0.01697 -0.0551 0.9190 0.0750
-4.750 -0.3767 0.02473 0.01657 -0.0522 0.9125 0.0773
-4.500 -0.3523 0.02423 0.01610 -0.0520 0.9085 0.0812
-4.250 -0.3225 0.02358 0.01546 -0.0529 0.9059 0.0867
-4.000 -0.2891 0.02299 0.01493 -0.0546 0.9039 0.0960
-3.750 -0.2759 0.02252 0.01454 -0.0526 0.8976 0.1049
-3.500 -0.2515 0.02189 0.01399 -0.0527 0.8929 0.1239
-3.250 -0.2215 0.02058 0.01320 -0.0544 0.8900 0.2153
-3.000 -0.1991 0.01902 0.01333 -0.0544 0.8878 0.5949
-2.750 -0.1870 0.01946 0.01378 -0.0512 0.8805 0.6258
-2.500 -0.1577 0.01998 0.01436 -0.0507 0.8759 0.6491
-2.250 -0.1195 0.02046 0.01482 -0.0516 0.8731 0.6654
-2.000 -0.0774 0.02095 0.01530 -0.0531 0.8712 0.6790
-1.750 -0.0695 0.02158 0.01593 -0.0490 0.8612 0.6887
-1.500 -0.0342 0.02206 0.01641 -0.0491 0.8581 0.6963
-1.250 0.0080 0.02209 0.01642 -0.0509 0.8561 0.7022
-1.000 0.0217 0.02230 0.01657 -0.0486 0.8469 0.7097
-0.750 0.0570 0.02238 0.01667 -0.0487 0.8433 0.7138
-0.500 0.1004 0.02210 0.01636 -0.0508 0.8412 0.7193
-0.250 0.1486 0.02150 0.01570 -0.0543 0.8397 0.7264
0.000 0.1526 0.02208 0.01632 -0.0494 0.8292 0.7303
0.250 0.1925 0.02168 0.01591 -0.0511 0.8268 0.7350
0.500 0.2384 0.02103 0.01519 -0.0548 0.8253 0.7407
0.750 0.2811 0.02050 0.01467 -0.0572 0.8240 0.7432
1.000 0.3302 0.01987 0.01404 -0.0607 0.8229 0.7454
1.250 0.3391 0.01993 0.01412 -0.0569 0.8119 0.7492
1.500 0.3860 0.01934 0.01352 -0.0604 0.8094 0.7532
1.750 0.4392 0.01875 0.01290 -0.0656 0.8075 0.7581
2.000 0.4958 0.01817 0.01234 -0.0707 0.8053 0.7598
2.250 0.4992 0.01816 0.01237 -0.0656 0.7934 0.7632
2.500 0.5578 0.01753 0.01173 -0.0712 0.7887 0.7662
2.750 0.5747 0.01730 0.01151 -0.0692 0.7765 0.7720
3.000 0.6249 0.01675 0.01095 -0.0732 0.7692 0.7748
3.250 0.6293 0.01661 0.01087 -0.0681 0.7562 0.7782
3.500 0.6447 0.01638 0.01067 -0.0654 0.7438 0.7826
3.750 0.6738 0.01608 0.01035 -0.0657 0.7312 0.7881
4.000 0.6995 0.01573 0.01002 -0.0648 0.7173 0.7913
4.250 0.7166 0.01551 0.00982 -0.0622 0.6997 0.7950
4.500 0.7329 0.01537 0.00966 -0.0597 0.6781 0.8001
4.750 0.7624 0.01519 0.00937 -0.0599 0.6513 0.8051
5.000 0.7762 0.01515 0.00928 -0.0568 0.6217 0.8088
5.250 0.7919 0.01524 0.00921 -0.0542 0.5836 0.8132
5.500 0.8065 0.01551 0.00925 -0.0518 0.5417 0.8178
5.750 0.8141 0.01585 0.00939 -0.0480 0.4955 0.8217
6.000 0.8188 0.01627 0.00960 -0.0437 0.4558 0.8257
6.250 0.8253 0.01678 0.00991 -0.0400 0.4225 0.8303
6.500 0.8363 0.01735 0.01029 -0.0374 0.3959 0.8349
6.750 0.8463 0.01779 0.01062 -0.0344 0.3734 0.8384
7.000 0.8573 0.01821 0.01099 -0.0317 0.3507 0.8422
7.250 0.8683 0.01870 0.01139 -0.0291 0.3262 0.8462
7.500 0.8788 0.01930 0.01187 -0.0266 0.3005 0.8503
7.750 0.8889 0.01977 0.01229 -0.0240 0.2717 0.8540
8.000 0.8974 0.02032 0.01274 -0.0211 0.2445 0.8582
8.250 0.9068 0.02099 0.01327 -0.0186 0.2230 0.8630
8.500 0.9179 0.02179 0.01393 -0.0165 0.2074 0.8674
8.750 0.9279 0.02246 0.01455 -0.0141 0.1954 0.8713
9.000 0.9387 0.02332 0.01529 -0.0121 0.1847 0.8754
9.250 0.9553 0.02392 0.01595 -0.0108 0.1754 0.8796
9.500 0.9712 0.02479 0.01670 -0.0096 0.1673 0.8831
9.750 0.9868 0.02533 0.01732 -0.0082 0.1601 0.8867
10.000 1.0063 0.02622 0.01807 -0.0076 0.1524 0.8902
10.250 1.0231 0.02681 0.01880 -0.0065 0.1467 0.8941
10.500 1.0405 0.02754 0.01951 -0.0057 0.1406 0.8980
10.750 1.0618 0.02833 0.02031 -0.0054 0.1350 0.9020
11.000 1.0780 0.02900 0.02110 -0.0044 0.1299 0.9065
11.250 1.0953 0.02975 0.02186 -0.0038 0.1253 0.9111
11.500 1.1168 0.03062 0.02275 -0.0037 0.1209 0.9156
11.750 1.1331 0.03137 0.02367 -0.0030 0.1166 0.9207
12.000 1.1498 0.03219 0.02454 -0.0025 0.1127 0.9260
12.250 1.1725 0.03320 0.02554 -0.0029 0.1086 0.9321
12.500 1.1911 0.03421 0.02676 -0.0031 0.1049 0.9412
12.750 1.2106 0.03518 0.02783 -0.0038 0.1010 0.9908
13.000 1.2257 0.03621 0.02876 -0.0027 0.0976 1.0000
13.250 1.2391 0.03754 0.03025 -0.0021 0.0944 1.0000
13.500 1.2506 0.03885 0.03168 -0.0013 0.0912 1.0000
13.750 1.2640 0.04009 0.03293 -0.0009 0.0881 1.0000
14.000 1.2843 0.04161 0.03442 -0.0010 0.0844 1.0000
14.250 1.2884 0.04323 0.03626 0.0002 0.0820 1.0000
14.500 1.2946 0.04483 0.03798 0.0011 0.0792 1.0000
14.750 1.3050 0.04625 0.03940 0.0016 0.0766 1.0000
15.000 1.3203 0.04797 0.04111 0.0017 0.0739 1.0000
15.250 1.3191 0.05008 0.04347 0.0029 0.0720 1.0000
15.500 1.3207 0.05217 0.04572 0.0036 0.0699 1.0000
15.750 1.3254 0.05404 0.04765 0.0041 0.0678 1.0000
16.000 1.3366 0.05564 0.04920 0.0042 0.0658 1.0000
16.250 1.3376 0.05831 0.05202 0.0046 0.0640 1.0000
16.500 1.3316 0.06135 0.05531 0.0050 0.0624 1.0000
16.750 1.3282 0.06430 0.05842 0.0050 0.0608 1.0000
17.000 1.3290 0.06694 0.06114 0.0048 0.0593 1.0000
17.250 1.3365 0.06893 0.06309 0.0046 0.0576 1.0000
17.500 1.3364 0.07212 0.06638 0.0043 0.0561 1.0000
17.750 1.3221 0.07672 0.07124 0.0034 0.0552 1.0000
18.000 1.3083 0.08154 0.07630 0.0021 0.0542 1.0000
18.250 1.2948 0.08659 0.08157 0.0004 0.0532 1.0000
18.500 1.2837 0.09143 0.08657 -0.0015 0.0521 1.0000
18.750 1.2799 0.09534 0.09055 -0.0033 0.0510 1.0000
19.000 1.2917 0.09693 0.09205 -0.0038 0.0496 1.0000
19.250 1.2789 0.10245 0.09771 -0.0062 0.0488 1.0000
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