EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.15 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e325-il-1000000.txt Download as CSV file: xf-e325-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5004 0.08119 0.07977 -0.0083 1.0000 0.0080
-10.250 -0.5227 0.06988 0.06842 -0.0162 1.0000 0.0080
-10.000 -0.5440 0.06311 0.06157 -0.0194 1.0000 0.0080
-9.750 -0.5692 0.05711 0.05547 -0.0204 1.0000 0.0080
-9.500 -0.5936 0.05184 0.05009 -0.0195 1.0000 0.0080
-9.250 -0.6138 0.04795 0.04610 -0.0173 1.0000 0.0080
-9.000 -0.6343 0.04404 0.04205 -0.0139 1.0000 0.0080
-8.750 -0.6575 0.03992 0.03776 -0.0088 1.0000 0.0080
-8.500 -0.6739 0.03673 0.03440 -0.0037 1.0000 0.0080
-8.250 -0.7056 0.03021 0.02759 0.0029 1.0000 0.0082
-7.500 -0.7647 0.02522 0.02108 0.0235 1.0000 0.0061
-7.000 -0.6645 0.01870 0.01493 0.0143 0.8068 0.0089
-6.750 -0.6539 0.01635 0.01224 0.0172 0.7784 0.0094
-6.000 -0.6023 0.01575 0.00973 0.0237 0.7409 0.0070
-5.750 -0.5773 0.01476 0.00855 0.0244 0.7186 0.0069
-5.500 -0.5532 0.01405 0.00770 0.0252 0.6980 0.0069
-5.250 -0.5297 0.01355 0.00709 0.0261 0.6782 0.0071
-5.000 -0.5069 0.01300 0.00644 0.0271 0.6603 0.0072
-4.750 -0.4842 0.01254 0.00588 0.0282 0.6436 0.0074
-4.500 -0.4609 0.01221 0.00547 0.0291 0.6283 0.0076
-4.250 -0.4379 0.01186 0.00503 0.0301 0.6136 0.0079
-4.000 -0.4162 0.01140 0.00448 0.0314 0.5990 0.0082
-3.750 -0.3933 0.01107 0.00409 0.0324 0.5857 0.0083
-3.500 -0.3709 0.01070 0.00365 0.0336 0.5734 0.0087
-3.250 -0.3472 0.01046 0.00335 0.0345 0.5605 0.0096
-3.000 -0.3236 0.01020 0.00303 0.0354 0.5484 0.0115
-2.750 -0.3015 0.00984 0.00272 0.0367 0.5373 0.0276
-2.500 -0.2803 0.00947 0.00251 0.0379 0.5268 0.0725
-2.250 -0.2589 0.00911 0.00234 0.0391 0.5159 0.1288
-2.000 -0.2437 0.00842 0.00210 0.0414 0.5065 0.2598
-1.750 -0.2434 0.00706 0.00170 0.0465 0.4986 0.5179
-1.500 -0.2493 0.00580 0.00149 0.0535 0.4920 0.7811
-1.250 -0.2259 0.00595 0.00169 0.0549 0.4824 0.8266
-1.000 -0.1995 0.00613 0.00184 0.0555 0.4731 0.8419
-0.750 -0.1730 0.00632 0.00197 0.0561 0.4637 0.8527
-0.500 -0.1453 0.00654 0.00217 0.0565 0.4551 0.8618
-0.250 -0.1181 0.00665 0.00222 0.0568 0.4466 0.8669
0.000 -0.0892 0.00686 0.00241 0.0569 0.4377 0.8726
0.250 -0.0623 0.00707 0.00257 0.0573 0.4300 0.8786
0.500 -0.0348 0.00711 0.00255 0.0574 0.4223 0.8812
0.750 -0.0068 0.00711 0.00249 0.0573 0.4147 0.8823
1.000 0.0216 0.00712 0.00246 0.0572 0.4072 0.8833
1.250 0.0497 0.00717 0.00245 0.0570 0.4002 0.8843
1.500 0.0780 0.00718 0.00244 0.0569 0.3937 0.8851
1.750 0.1058 0.00724 0.00243 0.0568 0.3865 0.8861
2.000 0.1341 0.00726 0.00244 0.0567 0.3805 0.8871
2.250 0.1620 0.00730 0.00244 0.0565 0.3743 0.8881
2.500 0.1899 0.00735 0.00245 0.0564 0.3684 0.8891
2.750 0.2180 0.00737 0.00245 0.0563 0.3625 0.8900
3.000 0.2456 0.00744 0.00248 0.0562 0.3564 0.8910
3.250 0.2735 0.00748 0.00251 0.0561 0.3515 0.8922
3.500 0.3014 0.00752 0.00253 0.0559 0.3456 0.8932
3.750 0.3288 0.00761 0.00257 0.0558 0.3395 0.8941
4.000 0.3570 0.00764 0.00261 0.0556 0.3347 0.8948
4.250 0.3847 0.00771 0.00265 0.0555 0.3287 0.8956
4.500 0.4122 0.00777 0.00269 0.0554 0.3229 0.8964
4.750 0.4401 0.00778 0.00272 0.0552 0.3176 0.8975
5.000 0.4675 0.00786 0.00279 0.0551 0.3115 0.8985
5.250 0.4951 0.00793 0.00287 0.0550 0.3064 0.8996
5.500 0.5227 0.00800 0.00295 0.0549 0.3005 0.9006
5.750 0.5497 0.00813 0.00306 0.0549 0.2939 0.9017
6.000 0.5775 0.00818 0.00314 0.0547 0.2887 0.9027
6.250 0.6046 0.00830 0.00325 0.0546 0.2819 0.9038
6.500 0.6318 0.00839 0.00336 0.0546 0.2757 0.9050
6.750 0.6588 0.00851 0.00347 0.0545 0.2682 0.9061
7.000 0.6857 0.00863 0.00360 0.0544 0.2608 0.9073
7.250 0.7123 0.00877 0.00373 0.0544 0.2530 0.9085
7.500 0.7389 0.00891 0.00388 0.0544 0.2456 0.9097
7.750 0.7651 0.00908 0.00405 0.0544 0.2369 0.9108
8.000 0.7914 0.00923 0.00421 0.0544 0.2287 0.9119
8.250 0.8169 0.00941 0.00438 0.0545 0.2190 0.9136
8.500 0.8421 0.00961 0.00458 0.0547 0.2086 0.9153
8.750 0.8669 0.00984 0.00481 0.0549 0.1963 0.9169
9.000 0.8912 0.01011 0.00506 0.0552 0.1834 0.9186
9.250 0.9144 0.01045 0.00536 0.0557 0.1681 0.9204
9.500 0.9362 0.01088 0.00572 0.0563 0.1501 0.9224
9.750 0.9575 0.01132 0.00610 0.0569 0.1318 0.9245
10.000 0.9789 0.01174 0.00649 0.0576 0.1186 0.9265
10.250 0.9982 0.01226 0.00694 0.0585 0.1023 0.9290
10.500 1.0158 0.01284 0.00746 0.0597 0.0863 0.9319
10.750 1.0320 0.01345 0.00801 0.0611 0.0704 0.9352
11.000 1.0493 0.01396 0.00851 0.0624 0.0618 0.9387
11.250 1.0645 0.01454 0.00907 0.0639 0.0527 0.9427
11.500 1.0786 0.01511 0.00965 0.0656 0.0457 0.9478
11.750 1.0914 0.01567 0.01023 0.0675 0.0394 0.9537
12.000 1.1027 0.01622 0.01082 0.0696 0.0347 0.9607
12.250 1.1127 0.01693 0.01155 0.0717 0.0299 0.9706
12.500 1.1333 0.01789 0.01254 0.0710 0.0251 0.9770
12.750 1.1540 0.01901 0.01368 0.0698 0.0208 0.9837
13.000 1.1779 0.02030 0.01502 0.0675 0.0175 0.9869
13.250 1.1992 0.02174 0.01653 0.0652 0.0153 0.9914
13.500 1.2172 0.02361 0.01845 0.0625 0.0132 0.9993
13.750 1.2163 0.02530 0.02021 0.0636 0.0126 1.0000
14.000 1.2150 0.02730 0.02227 0.0642 0.0118 1.0000
14.250 1.2127 0.02973 0.02476 0.0643 0.0110 1.0000
14.500 1.2092 0.03248 0.02760 0.0641 0.0104 1.0000
14.750 1.2090 0.03502 0.03021 0.0637 0.0098 1.0000
15.000 1.2052 0.03801 0.03330 0.0631 0.0097 1.0000
15.250 1.2009 0.04111 0.03645 0.0623 0.0089 1.0000
15.500 1.1916 0.04484 0.04025 0.0613 0.0082 1.0000
15.750 1.1851 0.04831 0.04381 0.0604 0.0081 1.0000
16.000 1.1738 0.05238 0.04798 0.0592 0.0081 1.0000
16.250 1.1656 0.05619 0.05188 0.0580 0.0079 1.0000
16.500 1.1552 0.06042 0.05621 0.0566 0.0079 1.0000
16.750 1.1493 0.06416 0.06003 0.0552 0.0076 1.0000
17.000 1.1403 0.06840 0.06435 0.0537 0.0073 1.0000
17.250 1.1305 0.07281 0.06883 0.0520 0.0071 1.0000
17.500 1.1220 0.07712 0.07321 0.0504 0.0068 1.0000
17.750 1.1103 0.08196 0.07814 0.0485 0.0067 1.0000
18.000 1.0995 0.08674 0.08300 0.0465 0.0064 1.0000
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