S3014-095-85 (s3014-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S3014-095-85 (s3014-il) Reynolds number: 200,000 Max Cl/Cd: 65.19 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3014-il-200000-n5.txt Download as CSV file: xf-s3014-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4468 0.10364 0.10012 -0.0157 1.0000 0.0200
-9.750 -0.4443 0.09960 0.09611 -0.0173 1.0000 0.0193
-9.500 -0.4431 0.09536 0.09190 -0.0194 1.0000 0.0190
-9.250 -0.4430 0.09093 0.08751 -0.0220 1.0000 0.0198
-9.000 -0.4448 0.08602 0.08265 -0.0250 1.0000 0.0204
-8.750 -0.4451 0.08193 0.07860 -0.0270 1.0000 0.0198
-8.500 -0.4482 0.07727 0.07400 -0.0300 1.0000 0.0199
-8.250 -0.4543 0.07243 0.06923 -0.0334 1.0000 0.0196
-8.000 -0.4623 0.06706 0.06391 -0.0381 1.0000 0.0192
-7.750 -0.4677 0.06047 0.05730 -0.0435 1.0000 0.0187
-7.500 -0.4734 0.05331 0.05001 -0.0474 0.9953 0.0182
-7.250 -0.4624 0.04323 0.03944 -0.0546 0.9763 0.0176
-7.000 -0.4479 0.03582 0.03140 -0.0578 0.9636 0.0173
-6.750 -0.4284 0.03117 0.02616 -0.0591 0.9541 0.0175
-6.500 -0.4074 0.02788 0.02236 -0.0593 0.9449 0.0178
-6.250 -0.3853 0.02556 0.01960 -0.0590 0.9363 0.0183
-6.000 -0.3612 0.02392 0.01759 -0.0587 0.9290 0.0195
-5.750 -0.3384 0.02229 0.01561 -0.0579 0.9207 0.0202
-5.500 -0.3143 0.02072 0.01371 -0.0571 0.9141 0.0203
-5.250 -0.2905 0.01940 0.01215 -0.0563 0.9061 0.0206
-5.000 -0.2660 0.01829 0.01082 -0.0555 0.8999 0.0209
-4.750 -0.2416 0.01734 0.00970 -0.0547 0.8921 0.0212
-4.250 -0.1934 0.01553 0.00768 -0.0530 0.8783 0.0223
-4.000 -0.1695 0.01480 0.00687 -0.0521 0.8721 0.0232
-3.750 -0.1445 0.01430 0.00634 -0.0516 0.8644 0.0253
-3.500 -0.1194 0.01388 0.00582 -0.0509 0.8582 0.0271
-3.250 -0.0937 0.01347 0.00530 -0.0503 0.8506 0.0282
-3.000 -0.0681 0.01312 0.00482 -0.0496 0.8442 0.0296
-2.750 -0.0421 0.01275 0.00442 -0.0491 0.8364 0.0333
-2.500 -0.0164 0.01238 0.00405 -0.0484 0.8299 0.0461
-2.250 0.0087 0.01188 0.00377 -0.0480 0.8217 0.1048
-2.000 0.0335 0.01141 0.00355 -0.0474 0.8151 0.1791
-1.750 0.0574 0.01081 0.00343 -0.0469 0.8063 0.3012
-1.500 0.0808 0.01029 0.00331 -0.0461 0.7990 0.4201
-1.250 0.1019 0.00966 0.00326 -0.0447 0.7903 0.5781
-1.000 0.1215 0.00904 0.00326 -0.0423 0.7821 0.7521
-0.750 0.1567 0.00877 0.00322 -0.0429 0.7740 0.8697
-0.500 0.2111 0.00869 0.00310 -0.0480 0.7644 0.9435
-0.250 0.2547 0.00867 0.00297 -0.0511 0.7538 0.9774
0.000 0.2971 0.00865 0.00282 -0.0540 0.7420 0.9984
0.250 0.3234 0.00867 0.00272 -0.0537 0.7295 1.0000
0.500 0.3479 0.00870 0.00265 -0.0529 0.7161 1.0000
0.750 0.3726 0.00875 0.00259 -0.0521 0.7022 1.0000
1.000 0.3974 0.00880 0.00255 -0.0514 0.6877 1.0000
1.250 0.4223 0.00887 0.00253 -0.0507 0.6728 1.0000
1.500 0.4473 0.00895 0.00252 -0.0500 0.6571 1.0000
1.750 0.4723 0.00905 0.00254 -0.0493 0.6407 1.0000
2.000 0.4972 0.00916 0.00256 -0.0486 0.6234 1.0000
2.250 0.5220 0.00929 0.00260 -0.0479 0.6053 1.0000
2.500 0.5469 0.00944 0.00266 -0.0472 0.5865 1.0000
2.750 0.5717 0.00960 0.00275 -0.0466 0.5659 1.0000
3.000 0.5963 0.00979 0.00284 -0.0459 0.5449 1.0000
3.250 0.6209 0.00999 0.00296 -0.0452 0.5218 1.0000
3.500 0.6453 0.01022 0.00309 -0.0445 0.4982 1.0000
3.750 0.6695 0.01048 0.00327 -0.0438 0.4733 1.0000
4.000 0.6935 0.01076 0.00345 -0.0431 0.4474 1.0000
4.250 0.7174 0.01106 0.00365 -0.0424 0.4212 1.0000
4.500 0.7411 0.01139 0.00388 -0.0417 0.3948 1.0000
4.750 0.7647 0.01173 0.00416 -0.0410 0.3692 1.0000
5.000 0.7881 0.01211 0.00444 -0.0403 0.3445 1.0000
5.250 0.8113 0.01249 0.00475 -0.0396 0.3212 1.0000
5.500 0.8346 0.01288 0.00508 -0.0390 0.2994 1.0000
5.750 0.8576 0.01330 0.00543 -0.0383 0.2794 1.0000
6.000 0.8807 0.01371 0.00583 -0.0376 0.2609 1.0000
6.250 0.9037 0.01412 0.00622 -0.0369 0.2435 1.0000
6.500 0.9265 0.01456 0.00663 -0.0362 0.2269 1.0000
6.750 0.9490 0.01500 0.00707 -0.0355 0.2117 1.0000
7.000 0.9713 0.01546 0.00752 -0.0347 0.1966 1.0000
7.250 0.9935 0.01594 0.00803 -0.0340 0.1823 1.0000
7.500 1.0152 0.01643 0.00853 -0.0332 0.1683 1.0000
7.750 1.0362 0.01699 0.00907 -0.0323 0.1528 1.0000
8.000 1.0570 0.01755 0.00961 -0.0314 0.1353 1.0000
8.250 1.0767 0.01819 0.01020 -0.0305 0.1164 1.0000
8.500 1.0959 0.01887 0.01083 -0.0294 0.1007 1.0000
8.750 1.1154 0.01951 0.01152 -0.0284 0.0890 1.0000
9.000 1.1332 0.02027 0.01225 -0.0272 0.0746 1.0000
9.250 1.1498 0.02112 0.01304 -0.0260 0.0569 1.0000
9.500 1.1640 0.02216 0.01397 -0.0244 0.0398 1.0000
9.750 1.1768 0.02326 0.01503 -0.0227 0.0257 1.0000
10.000 1.1865 0.02455 0.01629 -0.0206 0.0164 1.0000
10.250 1.1955 0.02567 0.01749 -0.0183 0.0132 1.0000
10.500 1.2016 0.02697 0.01887 -0.0157 0.0114 1.0000
10.750 1.2088 0.02822 0.02028 -0.0136 0.0107 1.0000
11.000 1.2154 0.02955 0.02177 -0.0115 0.0101 1.0000
11.250 1.2206 0.03104 0.02341 -0.0097 0.0097 1.0000
11.500 1.2244 0.03270 0.02522 -0.0079 0.0092 1.0000
11.750 1.2273 0.03450 0.02717 -0.0064 0.0087 1.0000
12.000 1.2294 0.03646 0.02927 -0.0052 0.0085 1.0000
12.250 1.2257 0.03906 0.03201 -0.0041 0.0079 1.0000
12.500 1.2206 0.04196 0.03506 -0.0033 0.0077 1.0000
12.750 1.2184 0.04476 0.03801 -0.0029 0.0075 1.0000
13.000 1.2164 0.04768 0.04110 -0.0029 0.0073 1.0000
13.250 1.2126 0.05099 0.04457 -0.0032 0.0071 1.0000
13.500 1.2067 0.05475 0.04849 -0.0039 0.0071 1.0000
13.750 1.1997 0.05885 0.05276 -0.0050 0.0069 1.0000
14.000 1.1919 0.06329 0.05736 -0.0064 0.0069 1.0000
14.250 1.1836 0.06802 0.06225 -0.0082 0.0068 1.0000
14.500 1.1752 0.07298 0.06737 -0.0102 0.0068 1.0000
14.750 1.1655 0.07841 0.07295 -0.0126 0.0068 1.0000
15.000 1.1558 0.08405 0.07878 -0.0153 0.0067 1.0000
15.250 1.1446 0.09015 0.08503 -0.0182 0.0067 1.0000
15.500 1.1351 0.09610 0.09113 -0.0212 0.0067 1.0000
15.750 1.1234 0.10269 0.09787 -0.0245 0.0066 1.0000
16.000 1.1131 0.10913 0.10445 -0.0278 0.0067 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S3014-095-85 (s3014-il)