USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.89 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa28-il-1000000-n5.txt Download as CSV file: xf-usa28-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 28 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9259 0.08460 0.08182 -0.0587 1.0000 0.0092
-16.500 -0.9575 0.07663 0.07375 -0.0627 1.0000 0.0093
-16.250 -0.9879 0.06927 0.06628 -0.0663 1.0000 0.0091
-16.000 -1.0278 0.06114 0.05803 -0.0702 1.0000 0.0089
-15.750 -1.0680 0.05355 0.05031 -0.0736 1.0000 0.0088
-15.500 -1.1212 0.04487 0.04150 -0.0775 1.0000 0.0086
-15.250 -1.1671 0.03267 0.02898 -0.0900 0.9989 0.0083
-15.000 -1.1643 0.02946 0.02559 -0.0922 0.9966 0.0085
-14.750 -1.1556 0.02757 0.02358 -0.0924 0.9945 0.0088
-14.500 -1.1449 0.02597 0.02189 -0.0918 0.9922 0.0093
-14.250 -1.1301 0.02463 0.02044 -0.0914 0.9900 0.0097
-14.000 -1.1112 0.02345 0.01918 -0.0915 0.9882 0.0103
-13.750 -1.0887 0.02242 0.01806 -0.0919 0.9868 0.0107
-13.500 -1.0635 0.02147 0.01702 -0.0927 0.9856 0.0112
-13.250 -1.0469 0.02058 0.01607 -0.0916 0.9827 0.0119
-13.000 -1.0272 0.01978 0.01522 -0.0909 0.9796 0.0127
-12.750 -1.0024 0.01904 0.01441 -0.0911 0.9774 0.0135
-12.500 -0.9755 0.01835 0.01365 -0.0917 0.9758 0.0143
-12.250 -0.9587 0.01776 0.01304 -0.0900 0.9717 0.0154
-12.000 -0.9373 0.01722 0.01247 -0.0892 0.9675 0.0165
-11.500 -0.8982 0.01628 0.01143 -0.0866 0.9553 0.0182
-11.250 -0.8809 0.01582 0.01094 -0.0847 0.9448 0.0191
-11.000 -0.8550 0.01535 0.01044 -0.0846 0.9367 0.0201
-10.750 -0.8238 0.01490 0.00995 -0.0856 0.9295 0.0212
-10.500 -0.7869 0.01442 0.00942 -0.0878 0.9242 0.0222
-10.250 -0.7456 0.01397 0.00889 -0.0910 0.9186 0.0230
-10.000 -0.7007 0.01356 0.00841 -0.0949 0.9131 0.0234
-9.750 -0.6558 0.01295 0.00772 -0.0992 0.9069 0.0249
-9.500 -0.6095 0.01255 0.00727 -0.1036 0.8987 0.0261
-9.250 -0.5626 0.01221 0.00685 -0.1081 0.8894 0.0271
-9.000 -0.5239 0.01196 0.00649 -0.1107 0.8750 0.0281
-8.750 -0.4943 0.01176 0.00617 -0.1113 0.8599 0.0287
-8.500 -0.4687 0.01161 0.00592 -0.1109 0.8466 0.0291
-8.250 -0.4446 0.01145 0.00570 -0.1102 0.8360 0.0295
-8.000 -0.4229 0.01112 0.00528 -0.1090 0.8278 0.0305
-7.750 -0.4003 0.01087 0.00496 -0.1080 0.8196 0.0313
-7.500 -0.3773 0.01065 0.00468 -0.1070 0.8117 0.0323
-7.250 -0.3541 0.01045 0.00443 -0.1061 0.8038 0.0331
-7.000 -0.3306 0.01027 0.00420 -0.1052 0.7967 0.0340
-6.750 -0.3070 0.01010 0.00397 -0.1042 0.7883 0.0346
-6.500 -0.2834 0.00995 0.00376 -0.1033 0.7803 0.0356
-6.250 -0.2598 0.00981 0.00356 -0.1024 0.7712 0.0361
-6.000 -0.2360 0.00967 0.00336 -0.1015 0.7623 0.0371
-5.750 -0.2132 0.00951 0.00315 -0.1004 0.7515 0.0390
-5.500 -0.1902 0.00937 0.00297 -0.0993 0.7391 0.0412
-5.250 -0.1674 0.00926 0.00281 -0.0982 0.7248 0.0440
-5.000 -0.1447 0.00916 0.00265 -0.0970 0.7097 0.0471
-4.750 -0.1225 0.00905 0.00249 -0.0957 0.6939 0.0525
-4.500 -0.0998 0.00897 0.00235 -0.0946 0.6787 0.0578
-4.250 -0.0768 0.00885 0.00220 -0.0935 0.6669 0.0660
-4.000 -0.0534 0.00872 0.00205 -0.0925 0.6576 0.0770
-3.750 -0.0310 0.00842 0.00190 -0.0915 0.6499 0.1196
-3.500 -0.0065 0.00835 0.00184 -0.0907 0.6433 0.1333
-3.250 0.0187 0.00829 0.00177 -0.0901 0.6367 0.1395
-3.000 0.0438 0.00825 0.00171 -0.0894 0.6310 0.1463
-2.750 0.0694 0.00823 0.00166 -0.0889 0.6264 0.1493
-2.500 0.0950 0.00818 0.00160 -0.0883 0.6212 0.1538
-2.250 0.1202 0.00813 0.00155 -0.0877 0.6164 0.1587
-1.750 0.1711 0.00805 0.00147 -0.0865 0.6084 0.1705
-1.500 0.1964 0.00798 0.00142 -0.0859 0.6037 0.1792
-1.250 0.2207 0.00791 0.00138 -0.0851 0.5983 0.1948
-1.000 0.2452 0.00781 0.00135 -0.0844 0.5932 0.2150
-0.750 0.2698 0.00771 0.00132 -0.0836 0.5880 0.2416
-0.500 0.2936 0.00764 0.00131 -0.0827 0.5818 0.2671
-0.250 0.3183 0.00760 0.00132 -0.0820 0.5756 0.2871
0.000 0.3430 0.00759 0.00133 -0.0812 0.5685 0.3007
0.250 0.3673 0.00759 0.00135 -0.0804 0.5613 0.3124
0.500 0.3916 0.00761 0.00136 -0.0796 0.5510 0.3202
0.750 0.4148 0.00766 0.00138 -0.0785 0.5366 0.3273
1.000 0.4356 0.00776 0.00140 -0.0769 0.5105 0.3327
1.250 0.4528 0.00799 0.00147 -0.0746 0.4705 0.3379
1.500 0.4729 0.00815 0.00155 -0.0729 0.4491 0.3442
1.750 0.4946 0.00827 0.00163 -0.0715 0.4368 0.3498
2.000 0.5163 0.00838 0.00171 -0.0702 0.4273 0.3549
2.250 0.5393 0.00844 0.00177 -0.0691 0.4212 0.3594
2.500 0.5621 0.00852 0.00184 -0.0680 0.4154 0.3633
2.750 0.5844 0.00860 0.00192 -0.0667 0.4106 0.3675
3.000 0.6077 0.00865 0.00200 -0.0657 0.4069 0.3713
3.250 0.6310 0.00871 0.00207 -0.0647 0.4029 0.3747
3.500 0.6538 0.00880 0.00216 -0.0636 0.3990 0.3777
3.750 0.6759 0.00891 0.00226 -0.0624 0.3945 0.3807
4.000 0.6989 0.00896 0.00236 -0.0613 0.3896 0.3850
4.250 0.7208 0.00907 0.00246 -0.0601 0.3828 0.3889
4.500 0.7423 0.00919 0.00258 -0.0587 0.3772 0.3933
4.750 0.7655 0.00925 0.00268 -0.0577 0.3740 0.3971
5.000 0.7881 0.00932 0.00280 -0.0566 0.3701 0.4015
5.250 0.8086 0.00947 0.00293 -0.0551 0.3618 0.4061
5.500 0.8317 0.00954 0.00304 -0.0541 0.3580 0.4093
5.750 0.8525 0.00967 0.00318 -0.0526 0.3481 0.4148
6.000 0.8729 0.00982 0.00332 -0.0511 0.3343 0.4204
6.500 0.9069 0.01032 0.00369 -0.0469 0.2895 0.4330
6.750 0.9188 0.01076 0.00399 -0.0439 0.2563 0.4392
7.000 0.9249 0.01143 0.00444 -0.0398 0.2092 0.4466
7.250 0.9329 0.01204 0.00488 -0.0361 0.1720 0.4559
7.500 0.9422 0.01259 0.00532 -0.0328 0.1408 0.4709
7.750 0.9513 0.01312 0.00579 -0.0295 0.1117 0.4996
8.250 1.1069 0.01508 0.00833 -0.0549 0.0187 0.9953
8.500 1.1343 0.01560 0.00884 -0.0555 0.0158 0.9984
8.750 1.1671 0.01610 0.00935 -0.0572 0.0141 0.9999
9.000 1.1824 0.01654 0.00980 -0.0552 0.0131 1.0000
9.250 1.1953 0.01700 0.01028 -0.0527 0.0123 1.0000
9.500 1.2070 0.01753 0.01083 -0.0501 0.0115 1.0000
9.750 1.2208 0.01798 0.01132 -0.0479 0.0110 1.0000
10.000 1.2337 0.01849 0.01186 -0.0456 0.0105 1.0000
10.250 1.2460 0.01905 0.01245 -0.0433 0.0101 1.0000
10.500 1.2579 0.01966 0.01309 -0.0410 0.0097 1.0000
10.750 1.2690 0.02035 0.01380 -0.0388 0.0092 1.0000
11.000 1.2793 0.02111 0.01461 -0.0365 0.0090 1.0000
11.250 1.2878 0.02200 0.01554 -0.0341 0.0085 1.0000
11.500 1.2990 0.02278 0.01637 -0.0321 0.0083 1.0000
11.750 1.3089 0.02367 0.01730 -0.0301 0.0081 1.0000
12.000 1.3190 0.02457 0.01825 -0.0282 0.0078 1.0000
12.250 1.3276 0.02562 0.01935 -0.0263 0.0077 1.0000
12.500 1.3374 0.02662 0.02040 -0.0246 0.0074 1.0000
12.750 1.3457 0.02775 0.02158 -0.0229 0.0071 1.0000
13.000 1.3528 0.02902 0.02291 -0.0211 0.0071 1.0000
13.250 1.3606 0.03027 0.02419 -0.0196 0.0067 1.0000
13.500 1.3667 0.03171 0.02569 -0.0180 0.0066 1.0000
13.750 1.3716 0.03329 0.02732 -0.0165 0.0065 1.0000
14.000 1.3722 0.03530 0.02940 -0.0149 0.0062 1.0000
14.250 1.3787 0.03687 0.03103 -0.0137 0.0061 1.0000
14.500 1.3824 0.03875 0.03299 -0.0126 0.0061 1.0000
14.750 1.3881 0.04050 0.03480 -0.0117 0.0059 1.0000
15.000 1.3905 0.04263 0.03701 -0.0107 0.0058 1.0000
15.250 1.3908 0.04503 0.03950 -0.0099 0.0058 1.0000
15.500 1.3954 0.04706 0.04159 -0.0093 0.0057 1.0000
15.750 1.3965 0.04950 0.04411 -0.0087 0.0056 1.0000
16.000 1.3965 0.05212 0.04680 -0.0082 0.0055 1.0000
16.250 1.3959 0.05487 0.04963 -0.0079 0.0054 1.0000
16.500 1.3963 0.05758 0.05242 -0.0076 0.0053 1.0000
16.750 1.3940 0.06064 0.05556 -0.0076 0.0052 1.0000
17.000 1.3909 0.06388 0.05889 -0.0076 0.0052 1.0000
17.250 1.3888 0.06710 0.06218 -0.0077 0.0051 1.0000
17.500 1.3827 0.07091 0.06609 -0.0081 0.0051 1.0000
17.750 1.3834 0.07391 0.06915 -0.0085 0.0049 1.0000
18.000 1.3769 0.07794 0.07328 -0.0092 0.0049 1.0000
18.250 1.3721 0.08181 0.07722 -0.0100 0.0048 1.0000
18.500 1.3662 0.08591 0.08142 -0.0109 0.0048 1.0000
18.750 1.3617 0.08983 0.08542 -0.0119 0.0047 1.0000
19.000 1.3518 0.09459 0.09026 -0.0131 0.0046 1.0000
19.250 1.3446 0.09897 0.09473 -0.0144 0.0046 1.0000
|
Polar data table (+)
Polar graphs
<< Back to USA 28 AIRFOIL (usa28-il)