S3021-095-84 (s3021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.73 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3021-il-1000000.txt Download as CSV file: xf-s3021-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S3021-095-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4055 0.08954 0.08794 -0.0275 1.0000 0.0117
-9.000 -0.4054 0.08534 0.08375 -0.0293 1.0000 0.0117
-7.500 -0.4458 0.04497 0.04323 -0.0554 0.9948 0.0121
-7.250 -0.4263 0.03983 0.03790 -0.0604 0.9887 0.0125
-7.000 -0.3990 0.03663 0.03454 -0.0643 0.9849 0.0128
-6.750 -0.3755 0.03307 0.03077 -0.0667 0.9766 0.0132
-6.500 -0.3516 0.02961 0.02705 -0.0684 0.9662 0.0138
-6.250 -0.3301 0.02643 0.02357 -0.0687 0.9505 0.0146
-6.000 -0.3058 0.02502 0.02188 -0.0680 0.9310 0.0160
-5.750 -0.2832 0.02450 0.02103 -0.0668 0.9071 0.0164
-5.500 -0.2747 0.01874 0.01466 -0.0651 0.8828 0.0177
-5.250 -0.2520 0.01762 0.01338 -0.0643 0.8622 0.0182
-5.000 -0.2285 0.01665 0.01221 -0.0635 0.8435 0.0190
-4.750 -0.2042 0.01566 0.01099 -0.0628 0.8266 0.0200
-4.500 -0.1813 0.01171 0.00641 -0.0605 0.8119 0.0137
-4.250 -0.1558 0.01106 0.00563 -0.0599 0.7973 0.0140
-3.750 -0.1043 0.00993 0.00426 -0.0589 0.7707 0.0141
-3.500 -0.0782 0.00950 0.00374 -0.0584 0.7585 0.0144
-3.250 -0.0517 0.00915 0.00331 -0.0580 0.7469 0.0149
-3.000 -0.0253 0.00881 0.00287 -0.0576 0.7360 0.0151
-2.750 0.0014 0.00852 0.00248 -0.0572 0.7254 0.0154
-2.500 0.0285 0.00827 0.00216 -0.0570 0.7150 0.0160
-2.250 0.0557 0.00807 0.00189 -0.0567 0.7050 0.0166
-2.000 0.0828 0.00787 0.00158 -0.0564 0.6953 0.0184
-1.750 0.1103 0.00773 0.00141 -0.0562 0.6855 0.0208
-1.500 0.1373 0.00750 0.00125 -0.0560 0.6761 0.0515
-1.250 0.1626 0.00698 0.00113 -0.0557 0.6667 0.1804
-1.000 0.1889 0.00665 0.00107 -0.0555 0.6568 0.2755
-0.750 0.2150 0.00634 0.00104 -0.0553 0.6477 0.3784
-0.500 0.2407 0.00605 0.00101 -0.0550 0.6384 0.4828
-0.250 0.2656 0.00564 0.00101 -0.0545 0.6292 0.6233
0.000 0.2829 0.00493 0.00108 -0.0520 0.6208 0.8719
0.250 0.3177 0.00491 0.00117 -0.0529 0.6113 0.9715
0.500 0.3549 0.00497 0.00118 -0.0549 0.6016 0.9839
0.750 0.3995 0.00504 0.00117 -0.0585 0.5912 0.9897
1.000 0.4409 0.00512 0.00117 -0.0615 0.5804 0.9955
1.250 0.4832 0.00516 0.00115 -0.0647 0.5691 0.9995
1.500 0.5107 0.00522 0.00116 -0.0646 0.5585 1.0000
1.750 0.5357 0.00529 0.00119 -0.0640 0.5475 1.0000
2.000 0.5607 0.00538 0.00122 -0.0634 0.5364 1.0000
2.250 0.5857 0.00546 0.00125 -0.0628 0.5246 1.0000
2.500 0.6108 0.00555 0.00130 -0.0622 0.5116 1.0000
2.750 0.6358 0.00566 0.00136 -0.0616 0.4986 1.0000
3.000 0.6608 0.00577 0.00142 -0.0610 0.4849 1.0000
3.250 0.6856 0.00590 0.00150 -0.0604 0.4699 1.0000
3.500 0.7104 0.00604 0.00159 -0.0597 0.4542 1.0000
4.000 0.7597 0.00636 0.00179 -0.0585 0.4201 1.0000
4.250 0.7842 0.00655 0.00191 -0.0578 0.4003 1.0000
4.500 0.8084 0.00676 0.00206 -0.0572 0.3805 1.0000
4.750 0.8327 0.00697 0.00220 -0.0565 0.3594 1.0000
5.000 0.8567 0.00723 0.00237 -0.0558 0.3379 1.0000
5.250 0.8798 0.00756 0.00257 -0.0550 0.3064 1.0000
5.500 0.9026 0.00796 0.00281 -0.0542 0.2711 1.0000
5.750 0.9257 0.00833 0.00306 -0.0534 0.2421 1.0000
6.000 0.9494 0.00866 0.00330 -0.0528 0.2203 1.0000
6.250 0.9726 0.00905 0.00357 -0.0521 0.1951 1.0000
6.500 0.9951 0.00950 0.00388 -0.0513 0.1657 1.0000
6.750 1.0169 0.01002 0.00424 -0.0504 0.1339 1.0000
7.000 1.0388 0.01053 0.00461 -0.0496 0.1073 1.0000
7.250 1.0586 0.01124 0.00511 -0.0485 0.0721 1.0000
7.500 1.0771 0.01208 0.00572 -0.0471 0.0378 1.0000
7.750 1.0935 0.01312 0.00656 -0.0454 0.0097 1.0000
8.000 1.1163 0.01353 0.00701 -0.0447 0.0088 1.0000
8.250 1.1382 0.01400 0.00753 -0.0438 0.0080 1.0000
8.500 1.1591 0.01455 0.00814 -0.0427 0.0074 1.0000
8.750 1.1777 0.01530 0.00899 -0.0413 0.0068 1.0000
9.000 1.1979 0.01587 0.00963 -0.0402 0.0066 1.0000
9.250 1.2177 0.01644 0.01025 -0.0391 0.0063 1.0000
9.500 1.2359 0.01710 0.01098 -0.0377 0.0062 1.0000
9.750 1.2523 0.01786 0.01182 -0.0361 0.0060 1.0000
10.000 1.2688 0.01855 0.01258 -0.0346 0.0058 1.0000
10.250 1.2823 0.01940 0.01351 -0.0326 0.0057 1.0000
10.500 1.2928 0.02023 0.01444 -0.0301 0.0057 1.0000
10.750 1.2993 0.02116 0.01545 -0.0270 0.0056 1.0000
11.000 1.3063 0.02211 0.01648 -0.0243 0.0054 1.0000
11.250 1.3112 0.02325 0.01771 -0.0215 0.0054 1.0000
11.500 1.3163 0.02445 0.01899 -0.0191 0.0053 1.0000
11.750 1.3201 0.02582 0.02044 -0.0169 0.0051 1.0000
12.000 1.3223 0.02743 0.02215 -0.0148 0.0051 1.0000
12.250 1.3239 0.02923 0.02403 -0.0131 0.0051 1.0000
12.500 1.3216 0.03149 0.02638 -0.0115 0.0049 1.0000
12.750 1.3169 0.03417 0.02916 -0.0102 0.0048 1.0000
13.000 1.3193 0.03633 0.03142 -0.0094 0.0048 1.0000
13.250 1.3102 0.03980 0.03501 -0.0084 0.0047 1.0000
13.500 1.3024 0.04334 0.03869 -0.0077 0.0046 1.0000
13.750 1.2931 0.04731 0.04282 -0.0070 0.0045 1.0000
14.000 1.2993 0.04932 0.04490 -0.0075 0.0046 1.0000
14.250 1.2900 0.05347 0.04924 -0.0079 0.0045 1.0000
14.750 1.2770 0.06149 0.05752 -0.0091 0.0045 1.0000
15.000 1.2704 0.06575 0.06191 -0.0097 0.0045 1.0000
15.250 1.2604 0.07069 0.06699 -0.0112 0.0045 1.0000
15.500 1.2563 0.07489 0.07130 -0.0130 0.0046 1.0000
15.750 1.2435 0.08073 0.07730 -0.0154 0.0046 1.0000
16.000 1.2387 0.08545 0.08212 -0.0178 0.0046 1.0000
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Polar data table (+)
Polar graphs
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