S3021-095-84 (s3021-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 200,000 Max Cl/Cd: 71.57 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3021-il-200000-n5.txt Download as CSV file: xf-s3021-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3968 0.07954 0.07620 -0.0325 1.0000 0.0316
-7.500 -0.4282 0.06412 0.06086 -0.0425 1.0000 0.0191
-7.250 -0.4317 0.06002 0.05676 -0.0435 1.0000 0.0187
-7.000 -0.4351 0.05581 0.05251 -0.0439 1.0000 0.0183
-6.750 -0.4173 0.04921 0.04567 -0.0496 0.9918 0.0176
-6.500 -0.3946 0.04143 0.03747 -0.0555 0.9818 0.0170
-6.250 -0.3714 0.03486 0.03036 -0.0589 0.9716 0.0165
-6.000 -0.3482 0.02993 0.02485 -0.0604 0.9598 0.0163
-5.750 -0.3227 0.02631 0.02068 -0.0612 0.9483 0.0163
-5.500 -0.2945 0.02377 0.01767 -0.0619 0.9375 0.0167
-5.250 -0.2645 0.02199 0.01549 -0.0626 0.9267 0.0179
-5.000 -0.2347 0.02030 0.01343 -0.0630 0.9150 0.0184
-4.750 -0.2057 0.01875 0.01157 -0.0632 0.9023 0.0184
-4.500 -0.1768 0.01748 0.01004 -0.0632 0.8891 0.0185
-4.250 -0.1487 0.01640 0.00878 -0.0631 0.8755 0.0187
-4.000 -0.1215 0.01551 0.00774 -0.0627 0.8616 0.0190
-3.750 -0.0951 0.01476 0.00686 -0.0622 0.8478 0.0193
-3.500 -0.0694 0.01407 0.00606 -0.0616 0.8340 0.0198
-3.250 -0.0441 0.01344 0.00529 -0.0610 0.8208 0.0208
-3.000 -0.0182 0.01301 0.00474 -0.0605 0.8080 0.0221
-2.750 0.0081 0.01271 0.00433 -0.0600 0.7957 0.0252
-2.500 0.0343 0.01241 0.00391 -0.0595 0.7839 0.0283
-2.250 0.0606 0.01211 0.00354 -0.0590 0.7723 0.0348
-2.000 0.0861 0.01165 0.00323 -0.0585 0.7611 0.0818
-1.750 0.1109 0.01115 0.00305 -0.0581 0.7504 0.1777
-1.500 0.1356 0.01070 0.00292 -0.0576 0.7402 0.2850
-1.250 0.1578 0.01003 0.00286 -0.0568 0.7299 0.4590
-1.000 0.1733 0.00901 0.00293 -0.0537 0.7202 0.7481
-0.750 0.2221 0.00878 0.00294 -0.0570 0.7108 0.9194
-0.500 0.2658 0.00883 0.00283 -0.0600 0.7005 0.9678
-0.250 0.3116 0.00885 0.00271 -0.0638 0.6899 0.9914
0.000 0.3472 0.00890 0.00261 -0.0655 0.6795 1.0000
0.250 0.3715 0.00898 0.00256 -0.0647 0.6695 1.0000
0.500 0.3960 0.00905 0.00254 -0.0640 0.6585 1.0000
0.750 0.4205 0.00914 0.00253 -0.0633 0.6477 1.0000
1.000 0.4451 0.00923 0.00253 -0.0625 0.6372 1.0000
1.250 0.4697 0.00934 0.00254 -0.0618 0.6269 1.0000
1.500 0.4944 0.00943 0.00258 -0.0612 0.6157 1.0000
1.750 0.5192 0.00954 0.00263 -0.0605 0.6047 1.0000
2.000 0.5439 0.00965 0.00269 -0.0598 0.5939 1.0000
2.250 0.5686 0.00978 0.00275 -0.0591 0.5827 1.0000
2.500 0.5933 0.00990 0.00283 -0.0584 0.5710 1.0000
2.750 0.6181 0.01003 0.00293 -0.0578 0.5587 1.0000
3.000 0.6429 0.01017 0.00304 -0.0571 0.5460 1.0000
3.250 0.6676 0.01032 0.00315 -0.0565 0.5327 1.0000
3.500 0.6922 0.01047 0.00328 -0.0558 0.5186 1.0000
3.750 0.7168 0.01064 0.00343 -0.0551 0.5039 1.0000
4.000 0.7412 0.01083 0.00359 -0.0544 0.4882 1.0000
4.250 0.7655 0.01103 0.00375 -0.0537 0.4717 1.0000
4.500 0.7897 0.01124 0.00394 -0.0530 0.4541 1.0000
4.750 0.8137 0.01148 0.00417 -0.0523 0.4351 1.0000
5.000 0.8373 0.01174 0.00439 -0.0515 0.4157 1.0000
5.250 0.8608 0.01203 0.00464 -0.0508 0.3948 1.0000
5.500 0.8839 0.01235 0.00492 -0.0500 0.3732 1.0000
5.750 0.9069 0.01269 0.00525 -0.0492 0.3510 1.0000
6.000 0.9291 0.01309 0.00559 -0.0483 0.3278 1.0000
6.250 0.9515 0.01349 0.00596 -0.0474 0.3054 1.0000
6.500 0.9734 0.01394 0.00636 -0.0465 0.2834 1.0000
6.750 0.9940 0.01448 0.00681 -0.0455 0.2551 1.0000
7.000 1.0136 0.01510 0.00733 -0.0444 0.2219 1.0000
7.250 1.0331 0.01575 0.00786 -0.0432 0.1919 1.0000
7.750 1.0693 0.01728 0.00908 -0.0408 0.1278 1.0000
8.000 1.0877 0.01802 0.00974 -0.0396 0.1059 1.0000
8.250 1.1048 0.01884 0.01047 -0.0382 0.0837 1.0000
8.500 1.1198 0.01984 0.01136 -0.0366 0.0568 1.0000
8.750 1.1330 0.02095 0.01234 -0.0348 0.0336 1.0000
9.000 1.1444 0.02218 0.01349 -0.0327 0.0187 1.0000
9.250 1.1570 0.02323 0.01457 -0.0308 0.0145 1.0000
9.500 1.1689 0.02425 0.01567 -0.0288 0.0123 1.0000
9.750 1.1769 0.02537 0.01689 -0.0262 0.0111 1.0000
10.000 1.1862 0.02639 0.01804 -0.0239 0.0108 1.0000
10.250 1.1942 0.02753 0.01932 -0.0217 0.0104 1.0000
10.500 1.2005 0.02882 0.02080 -0.0195 0.0101 1.0000
10.750 1.2056 0.03026 0.02238 -0.0174 0.0098 1.0000
11.000 1.2089 0.03191 0.02418 -0.0156 0.0095 1.0000
11.250 1.2115 0.03373 0.02614 -0.0140 0.0093 1.0000
11.500 1.2129 0.03576 0.02831 -0.0127 0.0091 1.0000
11.750 1.2129 0.03806 0.03076 -0.0116 0.0089 1.0000
12.000 1.2139 0.04039 0.03323 -0.0109 0.0088 1.0000
12.250 1.2123 0.04313 0.03609 -0.0103 0.0086 1.0000
12.500 1.2109 0.04598 0.03908 -0.0100 0.0085 1.0000
12.750 1.2100 0.04886 0.04209 -0.0100 0.0085 1.0000
13.000 1.2073 0.05209 0.04545 -0.0101 0.0084 1.0000
13.250 1.2039 0.05551 0.04901 -0.0104 0.0083 1.0000
13.500 1.2015 0.05890 0.05253 -0.0109 0.0082 1.0000
13.750 1.1981 0.06253 0.05632 -0.0115 0.0081 1.0000
14.000 1.1944 0.06632 0.06026 -0.0123 0.0081 1.0000
14.250 1.1893 0.07043 0.06450 -0.0135 0.0079 1.0000
14.500 1.1817 0.07502 0.06923 -0.0148 0.0077 1.0000
14.750 1.1773 0.07935 0.07372 -0.0163 0.0077 1.0000
15.000 1.1675 0.08467 0.07920 -0.0181 0.0075 1.0000
15.250 1.1593 0.09001 0.08469 -0.0204 0.0075 1.0000
15.500 1.1515 0.09553 0.09039 -0.0231 0.0074 1.0000
15.750 1.1422 0.10156 0.09661 -0.0262 0.0073 1.0000
16.000 1.1330 0.10769 0.10290 -0.0294 0.0074 1.0000
16.250 1.1232 0.11419 0.10957 -0.0330 0.0073 1.0000
16.500 1.1115 0.12147 0.11703 -0.0373 0.0072 1.0000
16.750 1.1006 0.12863 0.12434 -0.0414 0.0073 1.0000
17.000 1.0893 0.13610 0.13195 -0.0457 0.0073 1.0000
17.250 1.0766 0.14429 0.14030 -0.0507 0.0073 1.0000
17.500 1.0640 0.15280 0.14895 -0.0559 0.0074 1.0000
17.750 1.0512 0.16170 0.15797 -0.0613 0.0074 1.0000
18.000 1.0369 0.17157 0.16795 -0.0672 0.0074 1.0000
18.250 1.0224 0.18261 0.17914 -0.0736 0.0077 1.0000
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Polar data table (+)
Polar graphs
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