S8038 (13%) (s8038-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.82 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8038-il-1000000.txt Download as CSV file: xf-s8038-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7770 0.12500 0.12291 -0.0141 1.0000 0.0092
-16.500 -0.7898 0.11718 0.11501 -0.0182 1.0000 0.0092
-16.250 -0.8124 0.10771 0.10544 -0.0234 1.0000 0.0091
-16.000 -0.8717 0.09130 0.08880 -0.0327 1.0000 0.0089
-15.750 -0.8901 0.08341 0.08080 -0.0376 1.0000 0.0090
-15.500 -0.9227 0.07378 0.07098 -0.0432 1.0000 0.0088
-15.250 -0.9405 0.06700 0.06406 -0.0474 1.0000 0.0089
-15.000 -0.9517 0.06185 0.05877 -0.0504 1.0000 0.0089
-14.750 -0.9686 0.05630 0.05307 -0.0530 1.0000 0.0089
-14.500 -0.9766 0.05226 0.04890 -0.0549 1.0000 0.0090
-14.250 -0.9919 0.04761 0.04408 -0.0563 1.0000 0.0089
-14.000 -1.0007 0.04402 0.04035 -0.0570 1.0000 0.0090
-13.750 -1.0045 0.04125 0.03744 -0.0572 1.0000 0.0090
-13.500 -1.0056 0.03898 0.03505 -0.0570 1.0000 0.0091
-13.250 -1.0076 0.03671 0.03267 -0.0564 1.0000 0.0091
-13.000 -1.0073 0.03502 0.03085 -0.0555 1.0000 0.0091
-12.750 -1.0241 0.03124 0.02682 -0.0531 1.0000 0.0093
-12.500 -1.0252 0.02935 0.02481 -0.0510 1.0000 0.0094
-12.250 -1.0294 0.02724 0.02257 -0.0481 1.0000 0.0095
-12.000 -1.0269 0.02604 0.02129 -0.0454 1.0000 0.0096
-11.750 -1.0254 0.02496 0.02016 -0.0421 1.0000 0.0098
-11.500 -1.0248 0.02403 0.01916 -0.0381 1.0000 0.0098
-11.250 -1.0221 0.02335 0.01844 -0.0342 1.0000 0.0100
-11.000 -1.0148 0.02239 0.01739 -0.0312 1.0000 0.0100
-10.750 -1.0036 0.02172 0.01668 -0.0287 1.0000 0.0103
-10.500 -0.9926 0.02097 0.01587 -0.0262 1.0000 0.0104
-10.250 -0.9809 0.02025 0.01509 -0.0236 1.0000 0.0106
-10.000 -0.9674 0.01965 0.01445 -0.0213 1.0000 0.0109
-9.750 -0.9547 0.01896 0.01370 -0.0188 1.0000 0.0111
-9.500 -0.9410 0.01836 0.01305 -0.0165 1.0000 0.0113
-9.250 -0.9258 0.01791 0.01254 -0.0143 1.0000 0.0116
-9.000 -0.9122 0.01732 0.01190 -0.0119 1.0000 0.0117
-8.750 -0.8832 0.01664 0.01116 -0.0126 0.9987 0.0118
-8.500 -0.8535 0.01556 0.01000 -0.0138 0.9965 0.0121
-8.250 -0.8222 0.01465 0.00904 -0.0152 0.9945 0.0126
-8.000 -0.7911 0.01398 0.00833 -0.0163 0.9923 0.0130
-7.750 -0.7600 0.01342 0.00775 -0.0173 0.9892 0.0133
-7.500 -0.7269 0.01293 0.00723 -0.0186 0.9865 0.0138
-7.250 -0.6927 0.01246 0.00672 -0.0202 0.9844 0.0143
-7.000 -0.6619 0.01202 0.00626 -0.0210 0.9805 0.0148
-6.750 -0.6317 0.01155 0.00576 -0.0216 0.9754 0.0155
-6.500 -0.5984 0.01104 0.00523 -0.0230 0.9719 0.0165
-6.250 -0.5713 0.01066 0.00483 -0.0228 0.9637 0.0175
-6.000 -0.5379 0.01029 0.00445 -0.0240 0.9588 0.0187
-5.750 -0.5060 0.00988 0.00405 -0.0249 0.9506 0.0215
-5.500 -0.4664 0.00931 0.00358 -0.0277 0.9451 0.0395
-5.250 -0.4282 0.00874 0.00319 -0.0302 0.9353 0.0735
-5.000 -0.3900 0.00824 0.00285 -0.0328 0.9215 0.1125
-4.750 -0.3577 0.00786 0.00258 -0.0339 0.9020 0.1493
-4.500 -0.3311 0.00757 0.00236 -0.0337 0.8807 0.1881
-4.250 -0.3076 0.00728 0.00217 -0.0329 0.8596 0.2290
-4.000 -0.2844 0.00705 0.00201 -0.0319 0.8400 0.2690
-3.750 -0.2617 0.00681 0.00186 -0.0309 0.8218 0.3136
-3.500 -0.2391 0.00655 0.00172 -0.0298 0.8050 0.3627
-3.250 -0.2159 0.00633 0.00160 -0.0288 0.7900 0.4084
-3.000 -0.1931 0.00609 0.00150 -0.0278 0.7757 0.4619
-2.750 -0.1695 0.00590 0.00143 -0.0269 0.7623 0.5102
-2.500 -0.1446 0.00581 0.00139 -0.0262 0.7497 0.5423
-2.250 -0.1191 0.00577 0.00135 -0.0255 0.7377 0.5659
-2.000 -0.0931 0.00575 0.00133 -0.0250 0.7257 0.5854
-1.750 -0.0666 0.00573 0.00130 -0.0246 0.7141 0.5999
-1.500 -0.0400 0.00574 0.00128 -0.0242 0.7022 0.6123
-1.250 -0.0134 0.00577 0.00126 -0.0238 0.6901 0.6237
-1.000 0.0130 0.00577 0.00125 -0.0233 0.6781 0.6362
-0.750 0.0397 0.00577 0.00125 -0.0230 0.6669 0.6467
-0.500 0.0668 0.00580 0.00124 -0.0227 0.6560 0.6555
0.000 0.1202 0.00585 0.00123 -0.0220 0.6315 0.6728
0.250 0.1466 0.00587 0.00124 -0.0215 0.6170 0.6819
0.500 0.1732 0.00590 0.00125 -0.0212 0.6029 0.6909
0.750 0.1998 0.00594 0.00127 -0.0208 0.5891 0.6995
1.000 0.2264 0.00599 0.00128 -0.0204 0.5757 0.7072
1.250 0.2529 0.00603 0.00131 -0.0200 0.5617 0.7160
1.500 0.2793 0.00608 0.00134 -0.0196 0.5477 0.7248
1.750 0.3057 0.00615 0.00138 -0.0192 0.5331 0.7341
2.000 0.3318 0.00620 0.00142 -0.0188 0.5169 0.7426
2.250 0.3580 0.00628 0.00146 -0.0184 0.4987 0.7520
2.500 0.3832 0.00638 0.00153 -0.0177 0.4758 0.7618
2.750 0.4086 0.00649 0.00159 -0.0172 0.4555 0.7721
3.250 0.4586 0.00674 0.00175 -0.0159 0.4085 0.7946
3.500 0.4832 0.00689 0.00186 -0.0152 0.3831 0.8064
3.750 0.5075 0.00705 0.00197 -0.0145 0.3581 0.8191
4.000 0.5313 0.00723 0.00209 -0.0136 0.3315 0.8332
4.250 0.5545 0.00744 0.00224 -0.0127 0.3024 0.8488
4.500 0.5771 0.00767 0.00240 -0.0116 0.2721 0.8668
4.750 0.6002 0.00787 0.00257 -0.0107 0.2460 0.8878
5.000 0.6249 0.00807 0.00276 -0.0100 0.2221 0.9130
5.250 0.6576 0.00838 0.00301 -0.0112 0.1968 0.9392
5.500 0.6998 0.00873 0.00328 -0.0146 0.1738 0.9551
6.000 0.7785 0.00945 0.00383 -0.0201 0.1379 0.9745
6.250 0.8099 0.00976 0.00408 -0.0210 0.1262 0.9856
6.500 0.8437 0.01006 0.00434 -0.0225 0.1161 0.9923
6.750 0.8791 0.01037 0.00460 -0.0244 0.1055 0.9962
7.000 0.9152 0.01071 0.00488 -0.0265 0.0958 0.9991
7.250 0.9414 0.01097 0.00512 -0.0264 0.0901 1.0000
7.500 0.9594 0.01128 0.00539 -0.0245 0.0842 1.0000
7.750 0.9797 0.01147 0.00561 -0.0231 0.0818 1.0000
8.000 0.9992 0.01173 0.00586 -0.0215 0.0783 1.0000
8.250 1.0176 0.01207 0.00617 -0.0197 0.0737 1.0000
8.500 1.0374 0.01233 0.00645 -0.0182 0.0713 1.0000
8.750 1.0577 0.01256 0.00671 -0.0168 0.0694 1.0000
9.000 1.0771 0.01284 0.00700 -0.0153 0.0668 1.0000
9.250 1.0954 0.01318 0.00733 -0.0136 0.0639 1.0000
9.500 1.1122 0.01361 0.00777 -0.0116 0.0608 1.0000
9.750 1.1326 0.01383 0.00802 -0.0103 0.0597 1.0000
10.000 1.1521 0.01409 0.00832 -0.0089 0.0578 1.0000
10.250 1.1702 0.01441 0.00864 -0.0072 0.0554 1.0000
10.500 1.1864 0.01483 0.00905 -0.0053 0.0527 1.0000
10.750 1.2025 0.01524 0.00949 -0.0033 0.0504 1.0000
11.000 1.2206 0.01549 0.00977 -0.0017 0.0487 1.0000
11.250 1.2350 0.01583 0.01013 0.0006 0.0467 1.0000
11.500 1.2476 0.01625 0.01055 0.0032 0.0444 1.0000
11.750 1.2581 0.01682 0.01114 0.0059 0.0419 1.0000
12.000 1.2751 0.01712 0.01148 0.0076 0.0405 1.0000
12.250 1.2892 0.01759 0.01198 0.0096 0.0389 1.0000
12.500 1.3021 0.01814 0.01253 0.0117 0.0368 1.0000
12.750 1.3113 0.01891 0.01332 0.0141 0.0347 1.0000
13.000 1.3256 0.01944 0.01391 0.0158 0.0338 1.0000
13.250 1.3394 0.02001 0.01453 0.0174 0.0327 1.0000
13.500 1.3512 0.02073 0.01530 0.0191 0.0317 1.0000
13.750 1.3620 0.02156 0.01614 0.0208 0.0303 1.0000
14.000 1.3698 0.02262 0.01723 0.0226 0.0288 1.0000
14.250 1.3790 0.02365 0.01832 0.0241 0.0278 1.0000
14.500 1.3905 0.02457 0.01931 0.0252 0.0273 1.0000
14.750 1.4011 0.02560 0.02041 0.0262 0.0265 1.0000
15.000 1.4099 0.02683 0.02171 0.0273 0.0259 1.0000
15.250 1.4176 0.02821 0.02314 0.0281 0.0251 1.0000
15.500 1.4237 0.02979 0.02476 0.0289 0.0243 1.0000
15.750 1.4259 0.03179 0.02682 0.0296 0.0233 1.0000
16.000 1.4276 0.03393 0.02904 0.0301 0.0227 1.0000
16.250 1.4354 0.03556 0.03076 0.0303 0.0224 1.0000
16.500 1.4406 0.03750 0.03278 0.0304 0.0220 1.0000
16.750 1.4454 0.03950 0.03487 0.0305 0.0215 1.0000
17.000 1.4463 0.04200 0.03747 0.0303 0.0213 1.0000
17.250 1.4486 0.04441 0.03994 0.0300 0.0206 1.0000
17.500 1.4463 0.04738 0.04300 0.0296 0.0202 1.0000
17.750 1.4442 0.05045 0.04614 0.0289 0.0196 1.0000
18.000 1.4376 0.05417 0.04995 0.0279 0.0194 1.0000
18.250 1.4287 0.05831 0.05419 0.0266 0.0190 1.0000
18.500 1.4165 0.06304 0.05902 0.0249 0.0184 1.0000
18.750 1.4059 0.06768 0.06377 0.0232 0.0181 1.0000
19.000 1.3991 0.07187 0.06807 0.0215 0.0179 1.0000
19.250 1.3924 0.07613 0.07243 0.0199 0.0175 1.0000
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Polar data table (+)
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