REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 500,000 Max Cl/Cd: 76.45 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3-il-500000.txt Download as CSV file: xf-s3-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: REPUBLIC S-3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4687 0.08076 0.07877 -0.0097 1.0000 0.0229
-9.500 -0.4803 0.07346 0.07148 -0.0136 1.0000 0.0233
-9.250 -0.4997 0.06426 0.06230 -0.0200 1.0000 0.0229
-9.000 -0.5313 0.05601 0.05397 -0.0263 1.0000 0.0223
-8.750 -0.5606 0.05094 0.04882 -0.0282 1.0000 0.0220
-8.500 -0.5817 0.04719 0.04498 -0.0270 1.0000 0.0220
-8.250 -0.5918 0.04291 0.04055 -0.0263 1.0000 0.0223
-8.000 -0.5963 0.03856 0.03602 -0.0253 1.0000 0.0230
-7.750 -0.5921 0.03575 0.03278 -0.0232 1.0000 0.0250
-7.500 -0.5878 0.03205 0.02879 -0.0216 1.0000 0.0251
-7.250 -0.6094 0.04090 0.03709 -0.0191 1.0000 0.0252
-7.000 -0.6341 0.02236 0.01722 -0.0129 1.0000 0.0158
-6.750 -0.6143 0.02104 0.01577 -0.0116 1.0000 0.0162
-6.500 -0.5945 0.01982 0.01442 -0.0102 1.0000 0.0168
-6.250 -0.5748 0.01885 0.01332 -0.0087 1.0000 0.0177
-6.000 -0.5484 0.01749 0.01179 -0.0085 0.9971 0.0184
-5.750 -0.5113 0.01639 0.01051 -0.0103 0.9881 0.0191
-5.500 -0.4763 0.01431 0.00832 -0.0121 0.9778 0.0202
-5.250 -0.4385 0.01356 0.00755 -0.0143 0.9640 0.0217
-5.000 -0.4019 0.01301 0.00695 -0.0160 0.9449 0.0236
-4.750 -0.3716 0.01272 0.00656 -0.0163 0.9203 0.0252
-4.500 -0.3506 0.01172 0.00546 -0.0148 0.8947 0.0275
-4.250 -0.3267 0.01141 0.00507 -0.0138 0.8708 0.0302
-4.000 -0.3019 0.01120 0.00473 -0.0129 0.8507 0.0327
-3.750 -0.2786 0.01065 0.00413 -0.0119 0.8315 0.0381
-3.500 -0.2527 0.01049 0.00387 -0.0112 0.8142 0.0428
-3.250 -0.2280 0.01007 0.00340 -0.0105 0.7991 0.0515
-3.000 -0.2024 0.00980 0.00308 -0.0099 0.7851 0.0618
-2.750 -0.1766 0.00953 0.00279 -0.0093 0.7709 0.0778
-2.500 -0.1559 0.00846 0.00234 -0.0084 0.7577 0.2554
-2.250 -0.1370 0.00736 0.00210 -0.0072 0.7462 0.4930
-2.000 -0.1126 0.00706 0.00203 -0.0064 0.7352 0.5713
-1.750 -0.0871 0.00690 0.00198 -0.0057 0.7236 0.6220
-1.500 -0.0612 0.00680 0.00194 -0.0050 0.7101 0.6599
-1.250 -0.0353 0.00672 0.00191 -0.0044 0.6965 0.6960
-1.000 -0.0090 0.00668 0.00190 -0.0037 0.6835 0.7259
-0.750 0.0174 0.00665 0.00188 -0.0032 0.6701 0.7514
-0.500 0.0437 0.00663 0.00187 -0.0025 0.6549 0.7777
-0.250 0.0698 0.00661 0.00187 -0.0018 0.6367 0.8002
0.000 0.0962 0.00662 0.00183 -0.0013 0.6138 0.8164
0.250 0.1222 0.00666 0.00180 -0.0006 0.5831 0.8333
0.500 0.1476 0.00676 0.00178 0.0001 0.5416 0.8500
0.750 0.1726 0.00693 0.00178 0.0008 0.4940 0.8642
1.000 0.1978 0.00713 0.00182 0.0015 0.4518 0.8774
1.250 0.2233 0.00731 0.00189 0.0021 0.4236 0.8912
1.500 0.2493 0.00745 0.00196 0.0026 0.4026 0.9056
1.750 0.2761 0.00758 0.00204 0.0030 0.3835 0.9201
2.000 0.3047 0.00772 0.00211 0.0030 0.3639 0.9342
2.250 0.3359 0.00786 0.00219 0.0023 0.3428 0.9471
2.500 0.3696 0.00805 0.00228 0.0011 0.3209 0.9586
2.750 0.4042 0.00826 0.00238 -0.0004 0.3012 0.9691
3.000 0.4419 0.00848 0.00251 -0.0026 0.2839 0.9754
3.250 0.4774 0.00871 0.00266 -0.0043 0.2686 0.9830
3.500 0.5157 0.00893 0.00280 -0.0067 0.2532 0.9876
3.750 0.5524 0.00915 0.00296 -0.0088 0.2406 0.9937
4.000 0.5907 0.00938 0.00311 -0.0112 0.2292 0.9987
4.250 0.6172 0.00951 0.00323 -0.0112 0.2209 1.0000
4.500 0.6386 0.00972 0.00338 -0.0100 0.2140 1.0000
4.750 0.6616 0.00987 0.00353 -0.0092 0.2078 1.0000
5.000 0.6847 0.01009 0.00371 -0.0084 0.2021 1.0000
5.250 0.7088 0.01026 0.00389 -0.0077 0.1973 1.0000
5.500 0.7329 0.01045 0.00408 -0.0070 0.1921 1.0000
5.750 0.7568 0.01070 0.00428 -0.0064 0.1857 1.0000
6.000 0.7817 0.01085 0.00446 -0.0059 0.1800 1.0000
6.250 0.8057 0.01114 0.00470 -0.0053 0.1736 1.0000
6.500 0.8311 0.01129 0.00490 -0.0049 0.1681 1.0000
6.750 0.8558 0.01152 0.00512 -0.0044 0.1623 1.0000
7.000 0.8808 0.01175 0.00537 -0.0040 0.1563 1.0000
7.250 0.9059 0.01197 0.00558 -0.0036 0.1475 1.0000
7.500 0.9311 0.01218 0.00579 -0.0032 0.1359 1.0000
7.750 0.9554 0.01250 0.00604 -0.0028 0.1183 1.0000
8.000 0.9753 0.01336 0.00659 -0.0020 0.0761 1.0000
8.250 0.9963 0.01410 0.00721 -0.0012 0.0593 1.0000
8.500 1.0185 0.01468 0.00775 -0.0005 0.0478 1.0000
8.750 1.0363 0.01577 0.00865 0.0007 0.0193 1.0000
9.000 1.0571 0.01650 0.00945 0.0016 0.0170 1.0000
9.250 1.0781 0.01717 0.01023 0.0024 0.0155 1.0000
9.500 1.0986 0.01787 0.01105 0.0034 0.0146 1.0000
9.750 1.1184 0.01860 0.01190 0.0043 0.0141 1.0000
10.000 1.1363 0.01948 0.01291 0.0055 0.0132 1.0000
10.250 1.1527 0.02044 0.01398 0.0067 0.0127 1.0000
10.500 1.1660 0.02158 0.01523 0.0083 0.0122 1.0000
10.750 1.1764 0.02282 0.01658 0.0101 0.0119 1.0000
11.000 1.1804 0.02434 0.01821 0.0126 0.0115 1.0000
11.250 1.1757 0.02592 0.01990 0.0162 0.0113 1.0000
11.500 1.1672 0.02790 0.02200 0.0193 0.0111 1.0000
11.750 1.1605 0.03015 0.02436 0.0211 0.0110 1.0000
12.000 1.1552 0.03270 0.02702 0.0220 0.0109 1.0000
12.250 1.1538 0.03521 0.02963 0.0223 0.0109 1.0000
12.500 1.1544 0.03774 0.03227 0.0221 0.0108 1.0000
12.750 1.1543 0.04052 0.03516 0.0215 0.0106 1.0000
13.000 1.1506 0.04385 0.03859 0.0207 0.0106 1.0000
13.250 1.1485 0.04722 0.04207 0.0196 0.0105 1.0000
13.500 1.1441 0.05104 0.04601 0.0181 0.0102 1.0000
13.750 1.1404 0.05496 0.05004 0.0164 0.0101 1.0000
14.000 1.1355 0.05908 0.05426 0.0146 0.0100 1.0000
14.250 1.1306 0.06336 0.05864 0.0127 0.0098 1.0000
14.500 1.1254 0.06759 0.06297 0.0109 0.0098 1.0000
14.750 1.1201 0.07195 0.06742 0.0089 0.0096 1.0000
15.000 1.1153 0.07631 0.07187 0.0069 0.0096 1.0000
15.250 1.1103 0.08074 0.07638 0.0050 0.0094 1.0000
15.500 1.1063 0.08511 0.08084 0.0030 0.0093 1.0000
15.750 1.1028 0.08942 0.08525 0.0011 0.0094 1.0000
16.000 1.0989 0.09391 0.08983 -0.0010 0.0093 1.0000
16.250 1.0945 0.09857 0.09459 -0.0031 0.0093 1.0000
16.500 1.0905 0.10332 0.09943 -0.0056 0.0091 1.0000
16.750 1.0857 0.10829 0.10450 -0.0081 0.0092 1.0000
17.000 1.0803 0.11347 0.10978 -0.0107 0.0091 1.0000
17.250 1.0745 0.11889 0.11531 -0.0137 0.0091 1.0000
17.500 1.0674 0.12468 0.12122 -0.0169 0.0092 1.0000
17.750 1.0592 0.13085 0.12752 -0.0204 0.0092 1.0000
18.000 1.0501 0.13743 0.13423 -0.0242 0.0093 1.0000
18.250 1.0411 0.14413 0.14105 -0.0283 0.0094 1.0000
18.500 1.0312 0.15117 0.14821 -0.0325 0.0093 1.0000
18.750 1.0188 0.15910 0.15628 -0.0374 0.0095 1.0000
19.000 1.0056 0.16750 0.16480 -0.0425 0.0098 1.0000
19.250 0.9921 0.17632 0.17375 -0.0479 0.0098 1.0000
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